Federal Register / Vol. 70, No. 190 / Monday, October 3, 2005 / Rules and Regulations 57491 

(i) Remove from service any turbine wheel 

that has seal joint evidence present within 

blade fillet radii. 

Alternative Methods of Compliance 

(j) The Manager, Chicago Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Related Information 

(k) RRC Alert Service Bulletin No. CEB–A–

72–2205, dated April 26, 2005, pertains to 

the subject of this AD. 

Issued in Burlington, Massachusetts, on 

September 26, 2005. 

Francis A. Favara, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–19693 Filed 9–30–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20881; Directorate 

Identifier 2004–NM–253–AD; Amendment 

39–14302; AD 2003–17–07 R1] 

RIN 2120–AA64 

Airworthiness Directives; Various 

Transport Category Airplanes 

Manufactured by McDonnell Douglas 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is revising an 

existing airworthiness directive (AD) 

that applies to various transport 

category airplanes manufactured by 

McDonnell Douglas. We issued that AD 

to require a one-time test of the fire 

extinguishers for the engine and 

auxiliary power unit (APU), as 

applicable, to determine the capability 

of the Firex electrical circuits to fire 

discharge cartridges, and 

troubleshooting actions if necessary. 

This new AD removes certain transport 

category airplanes from the applicability 

of the existing AD. This AD results from 

reports indicating that fire extinguishers 

for the engine and auxiliary power unit 

had failed to discharge when 

commanded. We are issuing this AD to 

prevent failure of the fire extinguishers 

to fire discharge cartridges, which could 

result in the inability to put out a fire 

in an engine or in the APU. 

DATES: The effective date of this AD is 

September 24, 2003. 

On September 24, 2003 (68 FR 50058, 

August 20, 2003), the Director of the 

Federal Register approved the 

incorporation by reference of certain 

service bulletins listed in the AD. 

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, Long Beach Division, 3855 

Lakewood Boulevard, Long Beach, 

California 90846, Attention: Data and 

Service Management, Dept. C1–L5A 

(D800–0024) for service information 

identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Samuel Lee, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, 

Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

telephone (562) 627–5262; fax (562) 

627–5210. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may 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 street 

address stated in the ADDRESSES section. 

Discussion 

The FAA proposed to amend part 39 

of the Federal Aviation Regulations (14 

CFR part 39) with an airworthiness 

directive (AD) to revise AD 2003–17–07, 

amendment 39–13281 (68 FR 50058, 

August 20, 2003). The existing AD 

applies to various transport category 

airplanes manufactured by McDonnell 

Douglas. The proposed AD was 

published in the Federal Register on 

April 11, 2005 (70 FR 18324) to require 

a one-time test of the fire extinguishers 

for the engine and auxiliary power unit 

(APU), as applicable, to determine the 

capability of the Firex electrical circuits 

to fire discharge cartridges, and 

troubleshooting actions if necessary. 

That action also proposed to remove 

Model MD–10–10F and MD–10–30F 

airplanes from the applicability of the 

existing AD. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

No Objections to the NPRM 

One commenter states that it has no 

objection to the NPRM. 

Request To Give Credit for Previous 

Alternative Methods of Compliance 

(AMOCs) 

This same commenter notes that it has 

received an AMOC with AD 2003–17–

07. We infer that the commenter is 

requesting that credit be given for 

compliance with the AD in accordance 

with the AMOC. 

We acknowledge that the AMOC the 

commenter received provides 

compliance with AD 2003–17–07. 

However, it is unnecessary to amend 

this revised AD to reflect credit for 

previous accomplishment of the onetime test of the fire extinguishers for the 

engine and auxiliary power unit (APU), 

as applicable. This revised AD merely 

reduces the applicability of the AD, and 

all of the previous requirements, 

conditions, and provisions remain in 

effect. 

Request To Revise Note 1 

One commenter requests that we 

revise a typographical error in Note 1 of 

the proposed AD, which referred to 

paragraph (c) as the AMOC paragraph. 

We agree with the commenter, and have 

revised Note 1 to refer to paragraph (h) 

of the AD for AMOCs. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, 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 

There are about 3,311 airplanes of the 

affected design in the worldwide fleet. 

This AD will affect about 1,520 

airplanes of U.S. registry. 

The actions that are required by AD 

2003–17–07 and retained in this AD 

take between 4 work hours and 7 work 

hours per airplane, at an average labor 

rate of $65 per work hour. Based on 

these figures, the estimated cost of the 

currently required actions is estimated 

to be between $395,200, and $691,600, 

on U.S. operators, or between $260 and 

$455 per airplane. 

This AD does not add any new 

actions to the existing actions required 

by AD 2003–17–07. Since this AD will 

remove certain airplanes from the 

applicability of the AD, the total 

estimated cost of compliance of the AD 

for U.S. operators is actually reduced 

57492 Federal Register / Vol. 70, No. 190 / Monday, October 3, 2005 / Rules and Regulations 

from the existing AD. However, the 

estimated cost of compliance per 

airplane remains the same. 

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. 

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 and placed it in the AD docket. 

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, 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–13281 (68 

FR 50058, August 20, 2003) and adding 

the following new airworthiness 

directive (AD): 

2003–17–07 R1: Amendment 39–14302. 

Docket No. FAA–2005–20881; 

Directorate Identifier 2004–NM–253–AD. 

Effective Date 

(a) The effective date of this AD is 

September 24, 2003. 

Affected ADs 

(b) This AD revises AD 2003–17–07 to 

remove reference to McDonnell Douglas 

Model MD–10–10F and MD–10–30F 

airplanes. 

Applicability 

(c) This AD applies to the airplanes listed 

in Table 1 of this AD, certificated in any 

category. Table 1 of this AD follows: 

TABLE 1.—APPLICABILITY

McDonnell Douglas models As listed in 

Model DC–8–11, DC–8–12, DC–8–21, DC–8–31, DC–8–32, DC–8–33, 

DC–8–41, DC–8–42, and DC–8–43 airplanes; DC–8–51, DC–8–52, 

DC–8–53, and DC–8–55 airplanes; DC–8F–54 and DC–8F–55 airplanes; DC–8–61, DC–8–62, and DC–8–63 airplanes; DC–8–61F, 

DC–8–62F, and DC–8–63F airplanes; DC–8–71, DC–8–72 and DC– 

8–73 airplanes; DC–8–71F, DC–8–72F, and DC–8–73F airplanes.

Boeing Alert Service Bulletin DC8–26A042, including Appendix A, 

dated January 31, 2002. 

Model DC–9–11, DC–9–12, DC–9–13, DC–9–14, DC–9–15, and DC– 

9–15F airplanes; DC–9–21 airplanes; DC–9–31, DC–9–32, DC–9–32 

(VC–9C), DC–9–32F, DC–9–33F, DC–9–34, DC–9–34F, and DC–9– 

32F (C–9A, C–9B) airplanes; DC–9–41 airplanes; DC–9–51 airplanes; DC–9–81 (MD–81), DC–9–82 (MD–82), DC–9–83 (MD–83), 

and DC–9–87 (MD–87) airplanes; and MD–88 airplanes.

McDonnell Douglas Alert Service Bulletin DC9-26A029, Revision 01, 

dated May 8, 2001. 

Model DC–10–10 and DC–10–10F airplanes; DC–10–15 airplanes; 

DC–10–30 and DC–10–30F (KC–10A and KDC–10) airplanes; DC– 

10–40 and DC–10–40F airplanes;.

McDonnell Douglas Alert Service DC10–26A050, dated July 31, 2000. 

Model MD–11 and MD–11F airplanes ..................................................... McDonnell Douglas Alert Service Bulletin MD11–26A039, Revision 01, 

dated November 21, 2002. 

Model MD–90–30 airplanes ..................................................................... McDonnell Douglas Alert Service Bulletin MD90–26A005, dated July 

31, 2000. 

Unsafe Condition 

(d) This AD results from reports indicating 

that fire extinguishers for the engine and the 

auxiliary power unit (APU) had failed to 

discharge when commanded on a McDonnell 

Douglas Model DC–9–81 airplane and a 

Model DC–9–33F airplane. We are issuing 

this AD to prevent failure of the fire 

extinguishers to fire discharge cartridges, 

which could result in the inability to put out 

a fire in an engine or in the APU. 

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. 

Note 1: This AD applies to each airplane 

identified in the preceding applicability 

provision, regardless of whether it has been 

modified, altered, or repaired in the area 

subject to the requirements of this AD. For 

airplanes that have been modified, altered, or 

repaired so that the performance of the 

requirements of this AD is affected, the 

owner/operator must request approval for an 

alternative method of compliance in 

accordance with paragraph (h) of this AD. 

The request should include an assessment of 

the effect of the modification, alteration, or 

repair on the unsafe condition addressed by 

this AD; and, if the unsafe condition has not 

been eliminated, the request should include 

specific proposed actions to address it. 

Federal Register / Vol. 70, No. 190 / Monday, October 3, 2005 / Rules and Regulations 57493 

Testing the Firex Electrical Circuits 

(f) Within 18 months after the 

accumulation of 15,000 total flight hours, or 

within 18 months after September 24, 2003 

(the effective date of AD 2003–17–07), 

whichever occurs later: Test the capability of 

the electrical circuits of the Firex fire 

extinguishers for the engine and the APU, as 

applicable, per the applicable alert service 

bulletin (ASB) listed in Table 1 of this AD. 

(1) For any airplane equipped with an 

APU: If any electrical circuit of the Firex fire 

extinguishers for the APU does not pass the 

testing, before further flight, accomplish the 

troubleshooting procedures specified in the 

applicable ASB. Dispatch with an inoperative 

APU is permitted for the amount of time 

specified in the Minimum Equipment List. 

Dispatch after that time is not permitted until 

the circuits are repaired per the Boeing 

Standard Wiring Practices Manual (SWPM) 

D6–82481. 

(2) For all airplanes: If any electrical circuit 

of the Firex fire extinguishers for the engine 

does not pass the testing, before further 

flight, accomplish the troubleshooting 

procedures specified in the applicable ASB, 

and repair per SWPM D6–82481. Dispatch is 

not permitted until the circuits have been 

repaired. 

Actions Accomplished Per Previous Issue of 

Service Bulletins 

(g) Tests and troubleshooting procedures 

accomplished before the effective date of this 

AD per McDonnell Douglas Alert Service 

Bulletin DC9–26A029, dated July 27, 2000; or 

MD11–26A039, dated July 31, 2000; are 

considered acceptable for compliance with 

the corresponding action specified in 

paragraph (f) of this AD. 

Alternative Methods of Compliance 

(h) An alternative method of compliance or 

adjustment of the compliance time that 

provides an acceptable level of safety may be 

used if approved by the Manager, Los 

Angeles Aircraft Certification Office (ACO), 

FAA. Operators shall submit their requests 

through an appropriate FAA Principal 

Maintenance Inspector, who may add 

comments and then send it to the Manager, 

Los Angeles ACO. 

Note 2: Information concerning the 

existence of approved alternative methods of 

compliance with this AD, if any, may be 

obtained from the Los Angeles ACO. 

Special Flight Permits 

(i) Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the requirements of this AD 

can be accomplished. 

Material Incorporated by Reference 

(j) You must use the service bulletins listed 

in Table 2 of this AD to perform the actions 

that are required by this AD, unless the AD 

specifies otherwise. 

TABLE 2.—APPLICABLE SERVICE BULLETINS

Service bulletin Revision level Date 

Boeing Alert Service Bulletin DC8–26A042, including Appendix A .................................................. Original .................. January 31, 2002. 

McDonnell Douglas Alert Service Bulletin DC9–26A029 .................................................................. Revision 01 ............ May 8, 2001. 

McDonnell Douglas Alert Service Bulletin DC10–26A050 ................................................................ Original .................. July 31, 2000. 

McDonnell Douglas Alert Service Bulletin MD11–26A039 ............................................................... Revision 01 ............ November 21, 2002. 

McDonnell Douglas Alert Service Bulletin MD90–26A005 ............................................................... Original .................. July 31, 2000. 

(1) On September 24, 2003 (68 FR 50058, 

August 20, 2003), the Director of the Federal 

Register approved the incorporation by 

reference of Boeing and McDonnell Douglas 

service bulletins listed in Table 2. 

(2) Contact Boeing Commercial Airplanes, 

Long Beach Division, 3855 Lakewood 

Boulevard, Long Beach, California 90846, 

Attention: Data and Service Management, 

Dept. C1–L5A (D800–0024), for a copy of this 

service information. You may review copies 

at the Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street SW., Room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the NARA, call (202) 741–6030, 

or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html. 

Issued in Renton, Washington, on 

September 20, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19438 Filed 9–30–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22485; Directorate 

Identifier 2001–NM–337–AD; Amendment 

39–14293; AD 2005–19–28] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–301, –321, –322, –341, and –342 

Airplanes; and Model A340–200 and 

A340–300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A330–301, –321, –322, 

–341, and –342 airplanes; and Model 

A340–200 and A340–300 series 

airplanes. This AD requires repetitive 

inspections for cracks in the aft face of 

the rear spar at the area adjacent to the 

bolt holes and the end of the build slot, 

and repair if necessary. The AD also 

provides an optional terminating action 

for the repetitive inspections. This AD 

results from a report that, during fatigue 

tests of the wing, cracks were found in 

the vertical web of the rear spar between 

ribs 1 and 2 having initiated at the build 

slot. We are issuing this AD to detect 

and correct fatigue cracking in the 

vertical web of the wing rear spar, 

which could result in reduced structural 

integrity of the wing. 

DATES: Effective October 18, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 18, 2005. 

We must receive comments on this 

AD by December 2, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

Room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France,