Federal Register / Vol. 69, No. 26 / Monday, February 9, 2004 / Rules and Regulations 5911

Revision 04, dated November 27, 2001, is 

approved by the Director of the Federal 

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

and 1 CFR part 51. 

(2) The incorporation by reference of 

Airbus Service Bulletin A320–57–1051, 

Revision 01, dated March 21, 1996, was 

approved previously by the Director of the 

Federal Register as of April 3, 1998 (63 FR 

9934, February 27, 1998). 

(3) 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 Office of the Federal 

Register, 800 North Capitol Street, NW., suite 

700, Washington, DC.

Note 1: The subject of this AD is addressed 

in French airworthiness directive 2002–

340(B), dated June 26, 2002.

Effective Date 

(j) This amendment becomes effective on 

March 15, 2004.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2465 Filed 2–6–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2002–NM–320–AD; Amendment 

39–13449; AD 2004–03–05] 

RIN 2120–AA64

Airworthiness Directives; Boeing 

Model 777–200 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Model 777–200 

series airplanes. This action requires a 

surface high frequency eddy current 

inspection of the web of the aft pressure 

bulkhead, repetitive inspections, and 

corrective action, if necessary. This 

action is necessary to detect and correct 

cracks or damage to the web of the aft 

pressure bulkhead, which could enlarge 

if undetected, leading to rapid 

decompression of the airplane and 

consequent possible loss of flight 

critical systems. This action is intended 

to address the identified unsafe 

condition.

DATES: Effective February 24, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of February 

24, 2004. 

Comments for inclusion in the Rules 

Docket must be received on or before 

April 9, 2004.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2002–NM–

320–AD, 1601 Lind Avenue, SW., 

Renton, Washington 98055–4056. 

Comments may be inspected at this 

location between 9 a.m. and 3 p.m., 

Monday through Friday, except Federal 

holidays. Comments may be submitted 

via fax to (425) 227–1232. Comments 

may also be sent via the Internet using 

the following address: 9-anmiarcomment@faa.gov. Comments sent 

via fax or the Internet must contain 

‘‘Docket No. 2002–NM–320–AD’’ in the 

subject line and need not be submitted 

in triplicate. Comments sent via the 

Internet as attached electronic files must 

be formatted in Microsoft Word 97 or 

2000 or ASCII text. 

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 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue, SW., Renton, 

Washington; or at the Office of the 

Federal Register, 800 North Capitol 

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Gary 

Oltman, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 917–6443; 

fax (425) 917–6590.

SUPPLEMENTARY INFORMATION: The FAA 

received a report that parts of the radial 

lap splices at the station 2150 aft 

pressure bulkhead were covered up by 

a web repair made to the aft pressure 

bulkhead during production of two 

Boeing Model 777–200 series airplanes. 

The radial lap splices at the station 2150 

aft pressure bulkhead require repetitive 

inspections as an Airworthiness 

Limitation, which is defined as 

Structural Significant Item (SSI) 53–80–

I13 in Section 9 of Boeing Document 

D622W001, 777 Maintenance Planning 

Data. However, the web repairs made to 

the two Model 777–200 series airplanes 

could interfere with the detection of 

cracks or damage to the web during the 

required repetitive inspections. 

Undetected cracks or damage to the 

web, if not found and repaired, could 

result in the cracks enlarging, leading to 

rapid decompression of the airplane and 

consequent possible loss of flight 

critical systems. 

Explanation of Relevant Service 

Information 

The FAA has reviewed and approved 

Boeing Alert Service Bulletin 777–

53A0039, dated November 14, 2002, 

which describes procedures for a 

surface high frequency eddy current 

(HFEC) inspection of the web of the aft 

pressure bulkhead, repetitive 

inspections, and corrective action, if 

necessary. The corrective action 

involves repairing any crack or damage 

found during any surface HFEC 

inspection. The surface HFEC 

inspections required by this AD would 

replace repetitive inspections of the 

radial lap splices in the local area of the 

web repair, required as an 

Airworthiness Limitation, which is 

defined as SSI 53–80–I13 in Section 9 

of Boeing Document D622W001, 777 

Maintenance Planning Data. 

Accomplishment of the actions 

specified in the service bulletin is 

intended to adequately address the 

identified unsafe condition. 

Explanation of Requirements of the 

Rule 

Since an unsafe condition has been 

identified that is likely to exist or 

develop on other airplanes of the same 

type design that may be registered in the 

United States at some time in the future, 

this AD is being issued to detect and 

correct cracks or damage to the web of 

the aft pressure bulkhead, which could 

enlarge if undetected, leading to rapid 

decompression of the airplane and 

consequent possible loss of flight 

critical systems. This AD requires a 

surface HFEC inspection of the web of 

the aft pressure bulkhead, repetitive 

inspections, and corrective action, if 

necessary. The actions are required to be 

accomplished in accordance with the 

service bulletin described previously, 

except as discussed below. 

Difference Between Proposed Rule and 

Service Bulletin 

Operators should note that, although 

the service bulletin specifies that 

operators may contact the manufacturer 

for repair data if cracks or damage is 

found, this proposed AD would require 

operators to repair any crack or damage 

per a method approved by the FAA, or 

per data meeting the type certification 

basis of the airplane approved by a 

Boeing Company Designated 

Engineering Representative who has 

been authorized by the FAA to make 

such findings.

5912 Federal Register / Vol. 69, No. 26 / Monday, February 9, 2004 / Rules and Regulations 

Cost Impact 

None of the airplanes affected by this 

action are on the U.S. Register. All 

airplanes included in the applicability 

of this rule currently are operated by 

non-U.S. operators under foreign 

registry; therefore, they are not directly 

affected by this AD action. However, the 

FAA considers that this rule is 

necessary to ensure that the unsafe 

condition is addressed in the event that 

any of these subject airplanes are 

imported and placed on the U.S. 

Register in the future. 

Should an affected airplane be 

imported and placed on the U.S. 

Register in the future, it would require 

approximately between 2 and 4 work 

hours (depending on airplane 

configuration) to accomplish the 

required actions, at an average labor rate 

of $65 per work hour. Based on these 

figures, the cost impact of this AD 

would be between $130 and $260 per 

airplane (depending on airplane 

configuration). Manufacturer warranty 

remedies may be available for labor 

costs associated with this AD. As a 

result, the costs attributable to the AD 

may be less than stated above. 

Determination of Rule’s Effective Date 

Since this AD action does not affect 

any airplane that is currently on the 

U.S. register, it has no adverse economic 

impact and imposes no additional 

burden on any person. Therefore, prior 

notice and public procedures hereon are 

unnecessary and the amendment may be 

made effective in less than 30 days after 

publication in the Federal Register. 

Comments Invited 

Although this action is in the form of 

a final rule and was not preceded by 

notice and opportunity for public 

comment, comments are invited on this 

rule. Interested persons are invited to 

comment on this rule by submitting 

such written data, views, or arguments 

as they may desire. Communications 

shall identify the Rules Docket number 

and be submitted in triplicate to the 

address specified under the caption 

ADDRESSES. All communications 

received on or before the closing date 

for comments will be considered, and 

this rule may be amended in light of the 

comments received. Factual information 

that supports the commenter’s ideas and 

suggestions is extremely helpful in 

evaluating the effectiveness of the AD 

action and determining whether 

additional rulemaking action would be 

needed. 

Submit comments using the following 

format: 

• Organize comments issue-by-issue. 

For example, discuss a request to 

change the compliance time and a 

request to change the service bulletin 

reference as two separate issues. 

• For each issue, state what specific 

change to the AD is being requested. 

• Include justification (e.g., reasons or 

data) for each request. 

Comments are specifically invited on 

the overall regulatory, economic, 

environmental, and energy aspects of 

the rule that might suggest a need to 

modify the rule. All comments 

submitted will be available, both before 

and after the closing date for comments, 

in the Rules Docket for examination by 

interested persons. A report that 

summarizes each FAA-public contact 

concerned with the substance of this AD 

will be filed in the Rules Docket. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

submitted in response to this rule must 

submit a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket Number 2002–NM–320–AD.’’

The postcard will be date stamped and 

returned to the commenter. 

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:

2004–03–05 Boeing: Amendment 39–13449. 

Docket 2002–NM–320–AD.

Applicability: Model 777–200 series 

airplanes, variable numbers WA207 and 

WB325; certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously.

To detect and correct cracks or damage to 

the web of the aft pressure bulkhead, which 

could enlarge if undetected, leading to rapid 

decompression of the airplane and 

consequent possible loss of flight critical 

systems, accomplish the following: 

Initial and Repetitive Inspections 

(a) Prior to the accumulation of 30,000 total 

flight cycles, do a surface high frequency 

eddy current (HFEC) inspection to find 

cracks or damage to the web of the station 

2150 aft pressure bulkhead from the forward 

side, per the Accomplishment Instructions of 

Boeing Alert Service Bulletin 777–53A0039, 

dated November 14, 2002. Repeat the surface 

HFEC inspection thereafter at intervals not to 

exceed 16,000 flight cycles. 

Corrective Action 

(b) If any crack or damage is found during 

any surface HFEC inspection required by 

paragraph (a) of this AD, and the service 

bulletin specifies to ask Boeing for repair 

data: Before further flight, repair per a 

method approved by the Manager, Seattle 

Aircraft Certification Office (ACO), FAA; or 

per data meeting the type certification basis 

of the airplane approved by a Boeing 

Company Designated Engineering 

Representative who has been authorized by 

the Manager, Seattle ACO, to make such 

findings. For a repair method to be approved 

by the Manager, Seattle ACO, as required by 

this paragraph, the Manager’s approval letter 

must specifically refer to this AD. 

Alternative Methods of Compliance 

(c) In accordance with 14 CFR 39.19, the 

Manager, Seattle ACO, FAA, is authorized to 

approve alternative methods of compliance 

(AMOCs) for this AD. 

Incorporation by Reference 

(d) Unless otherwise specified by this AD, 

the actions shall be done in accordance with 

Boeing Alert Service Bulletin 777–53A0039, 

dated November 14, 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 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 Office of the Federal 

Federal Register / Vol. 69, No. 26 / Monday, February 9, 2004 / Rules and Regulations 5913

Register, 800 North Capitol Street, NW., suite 

700, Washington, DC. 

Effective Date 

(e) This amendment becomes effective on 

February 24, 2004.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2464 Filed 2–6–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2001–NM–355–AD; Amendment 

39–13448; AD 2004–03–04] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited 

(Jetstream) Model 4101 Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to all BAE Systems 

(Operations) Limited (Jetstream) Model 

4101 airplanes. This AD requires 

repetitive inspections for cracking in the 

casing of the nose landing gear (NLG), 

and corrective action if necessary. This 

action is necessary to find and fix 

cracking of the NLG casing, which could 

result in failure of the NLG, and 

consequent reduced controllability of 

the airplane during takeoff and landing. 

This action is intended to address the 

identified unsafe condition.

DATES: Effective March 15, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of March 15, 

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 Office of the 

Federal Register, 800 North Capitol 

Street, NW., suite 700, Washington, DC.

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 all BAE Systems 

(Operations) Limited (Jetstream) Model 

4101 airplanes was published in the 

Federal Register on November 18, 2003 

(68 FR 65011). That action proposed to 

require repetitive inspections for 

cracking in the casing of the nose 

landing gear, and corrective action if 

necessary. 

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 

We estimate that 57 airplanes of U.S. 

registry will be affected by this AD, and 

that it will take approximately 1 work 

hour per airplane to accomplish the 

required actions, at the average labor 

rate of $65 per work hour. Based on 

these figures, the cost impact of the 

requirements of this AD on U.S. 

operators is estimated to be $3,705, or 

$65 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:

2004–03–04 BAE Systems (Operations) 

Limited (Formerly British Aerospace 

Regional Aircraft): Amendment 39–

13448. Docket 2001–NM–355–AD.

Applicability: All Model Jetstream 4101 

airplanes, certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To find and fix cracking of the casing of 

the nose landing gear (NLG), which could 

result in failure of the NLG, and consequent 

reduced controllability of the airplane during 

takeoff and landing, accomplish the 

following: 

Service Bulletin References 

(a) The following information pertains to 

the service bulletin referenced in this AD: 

(1) The term ‘‘alert service bulletin’’ as 

used in this AD, means the Accomplishment 

Instructions of BAE Systems (Operations) 

Limited Alert Service Bulletin J41–A32–079, 

Revision 2, dated April 28, 2003. 

(2) The alert service bulletin refers to 

APPH Ltd. Service Bulletin AIR83586–32–18, 

Revision 1, dated October 2001, as an 

additional source of service information for 

the accomplishment of certain actions in