55326 Federal Register / Vol. 69, No. 177 / Tuesday, September 14, 2004 / Rules and Regulations 

Alert Service Bulletin DC10–24A149, 

Revision 04, dated March 26, 2003. 

Alternative Methods of Compliance 

(e) In accordance with 14 CFR 39.19, the 

Manager, Los Angeles Aircraft Certification 

Office, FAA, is authorized to approve 

alternative methods of compliance for this 

AD. 

Incorporation by Reference 

(f) The actions must be done in accordance 

with the applicable service bulletin listed in 

Table 1 of this AD.

TABLE 1.—SERVICE INFORMATION INCORPORATED BY REFERENCE

Service information Revision 

level Date 

McDonnell Douglas Alert Service Bulletin DC10–24A149 ............................................................................ 01 July 28, 1999. 

Boeing Alert Service Bulletin DC10–24A149 ................................................................................................ 02 April 5, 2001. 

Boeing Alert Service Bulletin DC10–24A149 ................................................................................................ 03 September 19, 2002. 

Boeing Alert Service Bulletin DC10–24A149 ................................................................................................ 04 March 26, 2003. 

(1) The incorporation by reference of 

Boeing Alert Service Bulletin DC10–24A149, 

Revision 03, dated September 19, 2002; and 

Boeing Alert Service Bulletin DC10–24A149, 

Revision 04, dated March 26, 2003; 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 

Boeing Alert Service Bulletin DC10–24A149, 

Revision 02, dated April 5, 2001, was 

approved previously by the Director of the 

Federal Register as of January 16, 2002 (66 FR 

64121, December 12, 2001). 

(3) The incorporation by reference of 

McDonnell Douglas Alert Service Bulletin 

DC10–24A149, Revision 01, dated July 28, 

1999, was approved previously by the 

Director of the Federal Register as of June 21, 

2000 (65 FR 31253, May 17, 2000). 

(4) Copies may be obtained from Boeing 

Commercial Aircraft Group, Long Beach 

Division, 3855 Lakewood Boulevard, Long 

Beach, California 90846, Attention: Data and 

Service Management, Dept. C1–L5A (D800–

0024). Copies may be inspected at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or at the 

FAA, Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, California; or at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at NARA, call (202) 741–

6030, or go to: http://www.archives.gov/

federal_register/code_of_federal_

regulations/ibr_locations.html.

Effective Date 

(g) This amendment becomes effective on 

October 19, 2004.

Issued in Renton, Washington, on August 

31, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–20406 Filed 9–13–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–228–AD; Amendment 

39–13793; AD 2004–18–14] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330 and Model A340–200 and –300 

Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to certain Airbus Model 

A330 and A340–200 and –300 series 

airplanes, that currently requires 

revising the Limitations Section of the 

airplane flight manual (AFM) to ensure 

that the flightcrew is advised of the 

proper procedures in the event of 

uncommanded movement of a spoiler 

during flight. This amendment adds 

inspections of the function of the 

pressure relief valves of each spoiler 

servo control (SSC), and corrective 

action if necessary. This new AD also 

mandates eventual modification of the 

SSCs, which terminates the AFM 

revision in the existing AD. The actions 

specified by this AD are intended to 

prevent uncommanded movement of a 

spoiler during flight, which could result 

in reduced controllability of the 

airplane and consequent significant 

increased fuel consumption during 

flight, which could necessitate an inflight turn-back or diversion to an 

unscheduled airport destination. This 

action is intended to address the 

identified unsafe condition.

DATES: Effective October 19, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of October 19, 

2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. 

This information may be examined at 

the Federal Aviation Administration 

(FAA), Transport Airplane Directorate, 

Rules Docket, 1601 Lind Avenue, SW., 

Renton, Washington; or at the National 

Archives and Records Administration 

(NARA). For information on the 

availability of this material at NARA, 

call (202) 741–6030, or go to: http://

www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html.

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2797; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 2002–16–12, 

amendment 39–12851 (67 FR 53478, 

August 16, 2002), which is applicable to 

certain Airbus Model A330 and A340 

series airplanes, was published in the 

Federal Register on April 1, 2004 (69 FR 

17091). The action proposed to continue 

to require revising the Limitations 

Section of the airplane flight manual 

(AFM) to ensure the flightcrew is 

advised of the proper procedures in the 

event of uncommanded movement of a 

spoiler during flight. The proposed AD 

also would require inspections and 

checks of the function of the pressure 

relief valves of each spoiler servo 

control (SSC), and corrective action if 

necessary. The proposed AD would also 

mandate eventual modification of the 

SSCs, which would terminate the AFM 

revision in the existing AD.

Comments 

Interested persons have been afforded 

an opportunity to participate in the

Federal Register / Vol. 69, No. 177 / Tuesday, September 14, 2004 / Rules and Regulations 55327

making of this amendment. Due 

consideration has been given to the 

comments received. 

One commenter supports the 

proposed AD. One commenter indicates 

that it does not own or operate any 

affected airplanes. 

Request To Change Applicability 

One commenter reiterates the 

applicability listed in the French 

airworthiness directives referenced in 

the proposed AD, and issued by the 

Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC), which is the airworthiness 

authority for France, and suggests that 

the applicability specified in the 

proposed AD be changed to match the 

French airworthiness directives. 

We do not agree. The applicability 

specified in the proposed AD was 

carried over from AD 2002–16–12, and 

has not changed. For clarification, the 

model designation listed on the type 

certificate data sheet, specifying Airbus 

Model A330 series airplanes, covers the 

airplane models identified as ‘‘Airbus 

Model A330–201, –202, –203, –223, 

–243, –301, –321, –322, –323, –341, 

–342, and –343 airplanes.’’ Airbus 

Model A340–200 and –300 series 

airplanes covers the airplane models 

identified as ‘‘Airbus Model A340–211, 

–212, –213, and A340–311, –312, and 

–313 airplanes.’’ In addition, the 

applicability in the proposed AD 

already specifies the part numbers for 

the SSCs, as does the effectivity in the 

French airworthiness directives. No 

change is made to the AD in this regard. 

Request To Clarify Paragraphs (c) and 

(d) of the Proposed AD 

One commenter states that the 

repetitive inspection intervals for SSCs 

with any malfunction, as specified in 

paragraph (c) of the proposed AD, and 

the repetitive inspection intervals for 

SSCs with no malfunction, as specified 

in paragraph (d) of the proposed AD, are 

redundant. 

Although the commenter does not 

make a specific request, we infer that 

the commenter is asking for clarification 

of the repetitive inspection intervals 

specified in paragraphs (c) and (d) of the 

proposed AD. We agree that some 

clarification is necessary; therefore, we 

have removed the repetitive inspection/

check intervals for functioning SSCs 

from paragraph (c), and included 

clarification that the requirements in 

paragraph (c) are only for affected SSCs 

on which a malfunction is found. In 

addition, we have included clarification 

that the repetitive inspections/checks 

required by paragraph (d) are only for 

affected SSCs on which no malfunction 

is found. 

Requests To Change Compliance Times 

One commenter states that there is a 

difference between the proposed AD 

and the referenced French airworthiness 

directives regarding the starting date for 

the initial detailed inspection/

functional check. The commenter also 

notes that there is a difference between 

the proposed AD and the referenced 

French airworthiness directives which 

provide a calendar date for 

accomplishment of the terminating 

action for all SSCs. 

Although the commenter does not 

make a specific request, we infer that 

the commenter is asking that the 

compliance time for the initial detailed 

inspection/functional check and the 

terminating action, as specified in 

paragraphs (b) and (e) of the proposed 

AD, respectively, be changed to match 

the compliance times in the French 

airworthiness directives. 

We do not agree. The French 

airworthiness directives give a 

compliance time for the initial detailed 

inspection/functional check based on 

the original issue date of those 

airworthiness directives. Due to some 

procedural differences in the way we 

express compliance times, the 

compliance time in this AD is presented 

in a manner that differs from that in the 

French airworthiness directives. 

However, the compliance time captures 

the intent of the French airworthiness 

directives, and ensures that operators of 

all affected airplanes are given sufficient 

time to accomplish the inspection, 

while still ensuring operational safety. 

In addition, the compliance time in 

the French airworthiness directives for 

the terminating action specifies a 

calendar time, but we do not express 

compliance times in terms of calendar 

dates unless an engineering analysis 

establishes a direct relationship between 

the date and the compliance time. 

Additionally, a risk assessment done by 

the manufacturer and the DGAC, in 

agreement with the FAA, validates the 

compliance times required by this AD. 

In light of these factors, we have 

determined that 700 flight hours for the 

initial detailed inspection/functional 

check, and 13 months for the 

terminating action, is appropriate. No 

change is made to the AD in this regard. 

Another commenter asks that the 

compliance time for the terminating 

action be extended. The commenter 

states that the actions required by the 

proposed AD are best suited for a base 

maintenance environment. The 

commenter adds that the current 

compliance time of 13 months for 

accomplishment of the modification of 

the SSCs does not coincide with any 

scheduled maintenance interval. The 

commenter asks that the compliance 

time be extended to 18 months to 

correspond with the C-check interval. 

We do not agree that the compliance 

time for the terminating action should 

be extended. As specified in our 

response above, a risk assessment done 

by the manufacturer and the DGAC, in 

agreement with the FAA, validates the 

compliance times required by this AD. 

No change is made to the AD in this 

regard. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

that have been submitted, 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.

Cost Impact 

There are about 14 airplanes of U.S. 

registry that will be affected by this AD. 

The AFM revision that is currently 

required by AD 2002–16–12 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 new inspections/checks that are 

required by 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 

inspections/checks required by this AD 

on U.S. operators is estimated to be 

$910, or $65 per airplane, per 

inspection/check cycle. 

The new modification that is required 

by this AD action will take about 15 

work hours per airplane to accomplish, 

at an average labor rate of $65 per work 

hour. Required parts will be provided to 

operators free of charge. Based on these 

figures, the cost impact of the 

modification required by this AD on 

U.S. operators is estimated to be 

$13,650, or $975 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 

55328 Federal Register / Vol. 69, No. 177 / Tuesday, September 14, 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. 

Currently, there are no Model A340 

series airplanes on the U.S. Register. 

However, if an affected airplane is 

imported and placed on the U.S. 

Register in the future, the new 

inspections/checks in this AD action 

would take about 1 work hour, at an 

average labor rate of $65 per work hour. 

Based on these figures, we estimate the 

cost of the inspections/checks to be $65 

per airplane, per inspection/check 

cycle. The new modification in this AD 

action would take about 15 work hours 

per airplane to accomplish, at an 

average labor rate of $65 per work hour. 

Required parts would be provided to 

operators free of charge. Based on these 

figures, we estimate the cost of this 

modification to be $975 per airplane. 

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 39–12851 (67 FR 

53478, August 16, 2002), and by adding 

a new airworthiness directive (AD), 

amendment 39–13793, to read as 

follows:

2004–18–14 Airbus: Amendment 39–13793. 

Docket 2002–NM–228–AD. Supersedes 

AD 2002–16–12, Amendment 39–12851.

Applicability: Model A330 and A340–200 

and –300 series airplanes, certificated in any 

category; equipped with any spoiler servo 

control having part number (P/N) 

1386A0000–01, 1386B0000–01, 1387A0000–

01, or 1387B0000–01. 

Compliance: Required as indicated, unless 

accomplished previously. 

To ensure that the flightcrew is advised of 

the proper procedures in the event of 

uncommanded movement of a spoiler during 

flight, which could result in reduced 

controllability of the airplane and consequent 

significant increased fuel consumption 

during flight, and could result in an in-flight 

turn-back or diversion to an unscheduled 

airport destination, accomplish the 

following: 

Restatement of Requirements of AD 2002–

16–12 

Revision to Airplane Flight Manual (AFM) 

(a) Within 10 days after September 20, 

2002 (the effective date of AD 2002–16–12, 

amendment 39–12851), revise the 

Limitations Section of the AFM by including 

the procedures listed in Figure 1 of this AD. 

This revision may be done by inserting a 

copy of the following Figure 1 into the AFM:

Figure 1

‘‘PROCEDURE:

∑ If ‘‘F/CTL SPLR FAULT’’ is triggered 

—F/CTL S/D 

page ................................................................................................................................................................................................. CHECK

∑ If the affected spoiler is not indicated extended amber: 

The spoiler is faulty in the retracted position. In such a case, the specific OEB procedure does not apply. 

—LDG DIST PROC .........................................................................................................................................................................

Multiply the landing distance by 1.1 for 3 or 4 spoilers lost per wing. 

Multiply the landing distance by 1.2 for 5 or 6 spoilers lost per wing. 

APPLY

∑ If the affected spoiler is indicated extended amber, apply the following procedure: 

IN CRUISE

CAUTION 

Disregard FMGC fuel predictions, as they do not take the increase in fuel consumption into account.

—FUEL CONSUMPTION INCREASE ...........................................................................................................................................

Apply 18.5% increase in the fuel consumption. 

APPLY 

—IN-FLIGHT TURN BACK/DIVERSION ......................................................................................................................................

In-flight turn back or diversion may have to be considered due to this fuel penalty. 

CONSIDER 

—MAX ACHIEVABLE ALTITUDE DECREASE ...........................................................................................................................

With the maximum spoiler deflection, the maximum altitude in ISA conditions may decrease by 4,500 feet. 

CONSIDER

FOR LANDING

—FOR LDG .....................................................................................................................................................................................

Use CONF 3 for landing to avoid possible buffeting, which, however, may be high depending on the failed spoiler. 

USE FLAP 3

—VAPP ........................................................................................................................................................................................... NORM 

—LDG DIST .................................................................................................................................................................................... x 1.1’’

Note 1: When the procedure in paragraph 

(a) of this AD has been incorporated into the 

general revisions of the AFM, the general 

revisions may be incorporated into the AFM, 

provided the procedures in this AD and the 

general revisions are identical. This AD may 

then be removed from the AFM.

New Requirements of This AD 

Initial Detailed Inspection/Functional Check 

(b) Within 700 flight hours after the 

effective date of this AD: Do a detailed 

Federal Register / Vol. 69, No. 177 / Tuesday, September 14, 2004 / Rules and Regulations 55329

inspection/functional check of the blocking 

function of the pressure relief valves (PRVs) 

of affected spoiler servo controls (SSCs) by 

doing all the actions in accordance with 

paragraphs 3.A., 3.B.(1)(a), 3.D., and 3.E. of 

the Accomplishment Instructions of Airbus 

Service Bulletin A330–27–3090 (for A330 

series airplanes) or A340–27–4096 (for A340–

200 and –300 series airplanes), both Revision 

02, both dated August 1, 2002, as applicable.

Note 2: 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. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Note 3: Liebherr Service Bulletin 1386A–

27–03, Revision 1, dated February 4, 2002, is 

referenced in Airbus Service Bulletins A330–

27–3090 and A340–27–4096, both Revision 

02, as an additional source of service 

information for accomplishment of the 

inspections.

Corrective Action 

(c) For airplanes having an affected SSC on 

which any malfunction is found during the 

inspection/functional check required by 

paragraph (a) of this AD: Before further flight, 

do the terminating action required by 

paragraph (e) of this AD for that SSC. 

(d) For airplanes having affected SSCs on 

which no malfunction is found during the 

inspection/functional check required by 

paragraph (a) of this AD: Repeat the 

inspection/functional check one time within 

1,600 flight hours after accomplishment of 

the initial inspection required by paragraph 

(a) of this AD. If no malfunction is found, 

repeat the inspection/functional check 

thereafter at intervals not to exceed 2,400 

flight hours, until accomplishment of the 

terminating action required by paragraph (e) 

of this AD. 

Terminating Action 

(e) Except as required by paragraph (c) of 

this AD: Within 13 months after the effective 

date of this AD, modify all affected SSCs by 

doing all the actions in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–27–3094 (for A330 

series airplanes) or A340–27–4100 (for A340–

200 and –300 series airplanes), both Revision 

01, both dated August 1, 2002; as applicable. 

Modification of all affected SSCs terminates 

the requirements of paragraphs (a), (b), (c), 

and (d) of this AD. After the modification has 

been done, the previously required AFM 

revision may be removed.

Note 4: Liebherr Service Bulletin 1386A–

27–05, dated February 25, 2002, is referenced 

in Airbus Service Bulletins A330–27–3094 

and A340–27–4100 as an additional source of 

service information for accomplishment of 

the modification.

Previously Accomplished Actions 

(f) Accomplishment of the inspections in 

accordance with Airbus Service Bulletins 

A330–27–3090 and A340–27–4096, both 

dated September 28, 2001; or A340–27–4096, 

Revision 01, dated December 12, 2001; as 

applicable; is considered acceptable for 

compliance with the inspections required by 

this AD.

(g) Airbus Service Bulletins A330–27–3090 

and A340–27–4096, both dated August 1, 

2002, specify to submit inspection results to 

the manufacturer, however; this AD does not 

include that requirement. 

Parts Installation 

(h) As of the effective date of this AD, no 

person may install on any airplane a spoiler 

servo control having P/N 1386A0000–01, 

1386B0000–01, 1387A0000–01, or 

1387B0000–01, unless it has been modified 

per paragraph (e) of this AD. 

Alternative Methods of Compliance 

(i) 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. 

Incorporation by Reference 

(j) The actions shall be done in accordance 

with the applicable service bulletins listed in 

Table 1 of this AD, unless the AD specifies 

otherwise.

TABLE 1.—MATERIALS INCORPORATED

BY REFERENCE

Airbus service 

bulletin 

Revision 

level Date 

A330–27–3090 02 Aug. 1, 2002. 

A330–27–3094 01 Aug. 1, 2002. 

A340–27–4096 02 Aug. 1, 2002. 

A340–27–4100 01 Aug. 1, 2002. 

The Director of the Federal Register approved 

the incorporation by reference of these 

documents in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. You can get copies 

of the documents from Airbus, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France. You can review copies at the Docket 

Management Facility, U.S. Department of 

Transportation, 400 Seventh Street SW., 

room PL–401, Nassif Building, Washington, 

DC; 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 5: The subject of this AD is addressed 

in French airworthiness directives 2002–

552(B) and 2002–553(B), both dated 

November 13, 2002.

Effective Date 

(k) This amendment becomes effective on 

October 19, 2004.

Issued in Renton, Washington, on August 

31, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–20407 Filed 9–13–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2000–NM–297–AD; Amendment 

39–13792; AD 2004–18–13] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B2 and B4 Series Airplanes; and 

Model A300 B4–601, B4–603, B4–605R, 

B4–620, B4–622R, C4–605R Variant F, 

and F4–605R Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to certain Airbus Model 

A300 B2 and B4 series airplanes, and 

Model A300 B4–601, B4–603, B4–605R, 

B4–620, B4–622R, C4–605R Variant F, 

and F4–605R airplanes, that currently 

requires a one-time inspection for 

cracking of the gantry lower flanges in 

the main landing gear (MLG) bay area; 

and repair, if necessary. This 

amendment removes an airplane model 

from the applicability. This amendment, 

for certain airplanes, retains the onetime inspection for cracking of the 

gantry lower flanges and repair, if 

necessary. For other airplanes, this 

amendment adds repetitive inspections 

of the gantry lower flanges; repair, if 

necessary; and reinforcement of the lefthand and right-hand gantry. The actions 

specified by this AD are intended to 

detect and correct cracking of the gantry 

lower flanges in the MLG bay area, 

which could result in decompression of 

the airplane. This action is intended to 

address the identified unsafe condition.

DATES: Effective October 19, 2004. 

The incorporation by reference of 

Airbus Service Bulletin A300–53–6128, 

dated March 5, 2001, as listed in the 

regulations, is approved by the Director 

of the Federal Register as of October 19, 

2004. 

The incorporation by reference of 

Airbus All Operators Telex (AOT) 53–

11, dated October 13, 1997, as listed in 

the regulations, was approved 

previously by the Director of the Federal 

Register as of July 30, 1998 (63 FR 

34589, June 25, 1998).