Federal Register / Vol. 69, No. 26 / Monday, February 9, 2004 / Rules and Regulations 5909

Optional Terminating Action 

(e) Modification of the structure around the 

fasteners that attach the pressure panel to the 

flexible bracket at frame 36, adjacent to the 

longitudinal beams on the left and right sides 

of the airplane, by accomplishing all 

applicable actions in accordance with 

paragraphs 3.A. through 3.E. of the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1029, Revision 01, 

dated April 29, 2002, constitutes terminating 

action for this AD. 

Credit for Actions Done per Previous Issue 

of Service Bulletins 

(f) Accomplishment of the required actions 

before the effective date of this AD in 

accordance with Airbus Service Bulletin 

A320–53–1030, dated January 5, 2000; or 

Airbus Service Bulletin A320–53–1029, 

dated January 5, 2000; is considered 

acceptable for compliance with the 

applicable requirements of paragraphs (a), 

(b), and (c) of this AD. 

Alternative Methods of Compliance 

(g) 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 

(h) Unless otherwise specified in this AD, 

the actions must be done in accordance with 

Airbus Service Bulletin A320–53–1030, 

Revision 01, excluding Appendix 01, dated 

May 21, 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 

Office of the Federal Register, 800 North 

Capitol Street, NW., suite 700, Washington, 

DC.

Note 3: The subject of this AD is addressed 

in French airworthiness directive 2000–531–

155(B), dated December 27, 2000.

Effective Date 

(i) 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. 04–2466 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–183–AD; Amendment 

39–13450; AD 2004–03–06] 

RIN 2120–AA64

Airworthiness Directives; Airbus Model 

A319 and A320 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to all Airbus Model A320 

series airplanes, that currently requires 

repetitive ultrasonic inspections to 

detect fatigue cracking in the wing/

fuselage joint cruciform fittings, and 

corrective actions if necessary. This 

amendment requires repetitive 

ultrasonic inspections for fatigue 

cracking in the wing/fuselage joint 

cruciform fittings at a reduced 

inspection threshold and repetitive 

interval. This amendment also adds 

airplanes to the applicability. The 

actions specified by this AD are 

intended to detect and correct fatigue 

cracks on the wing/fuselage joint 

cruciform fittings, which could result in 

reduced structural integrity of the wing/

fuselage. This action is intended to 

address the identified unsafe condition.

DATES: Effective March 15, 2004. 

The incorporation by reference of 

Airbus Service Bulletin A320–57–1051, 

Revision 04, dated November 27, 2001, 

as listed in the regulations, is approved 

by the Director of the Federal Register 

as of March 15, 2004. 

The incorporation by reference of 

Airbus Service Bulletin A320–57–1051, 

Revision 01, dated March 21, 1996, as 

listed in the regulations, was approved 

previously by the Director of the Federal 

Register as of April 3, 1998 (63 FR 9934, 

February 27, 1998).

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 Office of 

the Federal Register, 800 North Capitol 

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

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 98–04–49, 

amendment 39–10360 (63 FR 9934, 

February 27, 1998), which is applicable 

to all Airbus Model A320 series 

airplanes, was published in the Federal 

Register on December 4, 2003 (68 FR 

67814). The action proposed to require 

repetitive ultrasonic inspections for 

fatigue cracking in the wing/fuselage 

joint cruciform fittings at an inspection 

threshold and repetitive interval 

reduced from those in the existing AD. 

The action also proposed to add 

airplanes to the applicability of the 

existing AD. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. The FAA 

received no comments in response to 

the proposal or our determination of the 

cost to the public. 

Conclusion 

After careful review of the available 

data, we have determined that air safety 

and the public interest require the 

adoption of the rule as proposed. 

Cost Impact 

The actions that are currently 

required by AD 98–04–49 are applicable 

to 132 airplanes of U.S. registry and take 

approximately 2 work hours per 

airplane to accomplish (not including 

time for gaining access and closing up), 

at an average labor rate of $65 per work 

hour. Based on these figures, the cost 

impact of the currently required actions 

on U.S. operators is estimated to be 

$17,160, or $130 per airplane. 

This new AD affects approximately 

475 airplanes of U.S. registry. The new 

actions that are required by this AD take 

approximately 2 work hours per 

airplane to accomplish, at an average 

labor rate of $65 per work hour. Based 

on these figures, the cost impact of the 

new requirements of this AD on U.S. 

operators is estimated to be $61,750, or 

$130 per airplane. 

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 

5910 Federal Register / Vol. 69, No. 26 / Monday, February 9, 2004 / Rules and Regulations 

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 39–10360 (63 FR 

9934, February 27, 1998), and by adding 

a new airworthiness directive (AD), 

amendment 39–13450, to read as 

follows:

2004–03–06 Airbus: Amendment 39–13450. 

Docket 2002–NM–183–AD. Supersedes 

AD 98–04–49, Amendment 39–10360.

Applicability: All Model A319 and A320 

series airplanes, certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously.

To detect and correct fatigue cracks on the 

wing/fuselage joint cruciform fittings, which 

could result in reduced structural integrity of 

the wing/fuselage, accomplish the following: 

Requirements of AD 98–04–49

Ultrasonic Inspection (Model A320 Series 

Airplanes) 

(a) For Model A320 series airplanes: Prior 

to the accumulation of 28,000 total landings, 

or within 60 days after April 3, 1998 (the 

effective date of AD 98–04–49, amendment 

39–10360), whichever occurs later, perform 

an ultrasonic inspection to detect fatigue 

cracking in the wing/fuselage joint cruciform 

fittings, in accordance with Airbus Service 

Bulletin A320–57–1051, Revision 01, dated 

March 21, 1996. 

(1) If no cracking is detected, repeat the 

inspection thereafter at intervals not to 

exceed 20,000 landings, until paragraph (c) of 

this AD is accomplished. 

(2) If any crack is detected, prior to further 

flight, repair it in accordance with the service 

bulletin. Thereafter, repeat the inspection at 

the times specified in paragraph (a)(2)(i) or 

(a)(2)(ii) of this AD, as applicable. 

(i) If the crack that was detected and 

repaired was greater than 2.5 mm: Repeat the 

inspection prior to the accumulation of 

32,000 landings since accomplishment of the 

repair; and thereafter at intervals not to 

exceed 32,000 landings. 

(ii) If the crack that was detected and 

repaired was less than or equal to 2.5 mm: 

Repeat the inspection prior to the 

accumulation of 28,000 landings since 

accomplishment of the repair; and thereafter 

at intervals not to exceed 20,000 landings. 

New Requirements of This AD 

Ultrasonic Inspection (Model A319 Series 

Airplanes) 

(b) For Model A319 series airplanes: 

Perform an ultrasonic inspection to detect 

fatigue cracking in the wing/fuselage joint 

cruciform fittings, in accordance with Airbus 

Service Bulletin A320–57–1051, Revision 04, 

dated November 27, 2001. Do the initial 

inspection at the later of the times specified 

in paragraphs (b)(1) and (b)(2) of this AD. 

Repeat the inspection thereafter at intervals 

not to exceed the applicable interval 

specified in paragraph 1.E.(2) of the service 

bulletin. 

(1) Prior to the accumulation of 20,000 

total flight cycles or 42,000 total flight hours, 

whichever is first. 

(2) Prior to the accumulation of 28,000 

total flight cycles or within 3,500 flight 

cycles after the effective date of this AD, 

whichever is first. 

Ultrasonic Inspection (Model A320 Series 

Airplanes) 

(c) For Model A320 series airplanes: 

Perform an ultrasonic inspection to detect 

fatigue cracking in the wing/fuselage joint 

cruciform fittings, in accordance with Airbus 

Service Bulletin A320–57–1051, Revision 04, 

dated November 27, 2001, at the later of the 

times specified in paragraphs (c)(1) and (c)(2) 

of this AD, except as required by paragraph 

(f) of this AD. Accomplishment of the 

inspection required by this paragraph 

terminates the repetitive inspections required 

by paragraph (a) of this AD. Except as 

required by paragraph (e) of this AD, repeat 

the ultrasonic inspection at intervals not to 

exceed the applicable interval specified in 

paragraph 1.E.(2) of the service bulletin. 

(1) Prior to the accumulation of 20,000 

total flight cycles or 42,000 total flight hours, 

whichever is first. 

(2) Prior to the accumulation of 28,000 

total flight cycles or within 3,500 flight 

cycles after the effective date of this AD, 

whichever is first. 

Cracking: Corrective Action and Repeat 

Inspections 

(d) If any crack is found during any 

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

this AD: Before further flight, do all 

applicable actions in paragraphs B.(1)(b), 

C.(1), D., and E. (including removing the 

fastener, performing a rotative probe 

inspection to confirm the crack or determine 

the size of the crack, and accomplishing 

applicable corrective actions) of the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1051, Revision 04, 

dated November 27, 2001, except as provided 

by paragraph (e) of this AD. 

(e) If any crack is found during any 

inspection required by this AD, and the 

service bulletin recommends contacting 

Airbus for appropriate action: Before further 

flight, repair and perform repetitive 

inspections per a method and at a repetitive 

inspection interval approved by the Manager, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate; or the 

Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC) (or its delegated agent). 

Model A320 Series Airplanes Repaired 

Previously 

(f) For Model A320 series airplanes on 

which a crack measuring more than 2.5 mm 

was repaired prior to the effective date of this 

AD per Airbus Service Bulletin A320–57–

1051, Revision 01, dated March 21, 1996: 

Perform repetitive inspections per a method 

and at an interval approved by the Manager, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate; or the 

Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC) (or its delegated agent). 

Reporting of Inspection Results Not Required 

(g) Where the Accomplishment 

Instructions of Airbus Service Bulletin A320–

57–1051, Revision 04, dated November 27, 

2001, describe procedures for reporting 

inspection results to Airbus, this AD does not 

require such reporting.

Alternative Methods of Compliance 

(h) 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 

(i) Unless otherwise provided by this AD, 

the actions shall be done in accordance with 

Airbus Service Bulletin A320–57–1051, 

Revision 01, dated March 21, 1996; and 

Airbus Service Bulletin A320–57–1051, 

Revision 04, dated November 27, 2001; as 

applicable. 

(1) The incorporation by reference of 

Airbus Service Bulletin A320–57–1051, 

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.