5924 Federal Register / Vol. 69, No. 26 / Monday, February 9, 2004 / Rules and Regulations 

delegated agent). If the cracking is repaired, 

repeat the inspections as required by 

paragraph (c) of this AD. 

Modification 

(e) Modification of the transition and pickup angles in the lower part of the center 

fuselage in accordance with paragraphs 3.A. 

through 3.D. of the Accomplishment 

Instructions of Airbus Service Bulletin A320–

53–1027, Revision 03, dated February 12, 

2002, ends the repetitive inspections 

required by this AD. 

Alternative Methods of Compliance 

(f) 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 

(g) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Airbus Service Bulletin A320–53–1027, 

Revision 2, dated June 8, 1995; Airbus 

Service Bulletin A320–53–1027, Revision 03, 

dated February 12, 2002; Airbus Service 

Bulletin A320–53–1028, dated March 1, 

1994; and Airbus Service Bulletin A320–53–

1028, Revision 01, dated February 12, 2002; 

as applicable. 

(1) The incorporation by reference of 

Airbus Service Bulletin A320–53–1027, 

Revision 03, dated February 12, 2002; and 

Airbus Service Bulletin A320–53–1028, 

Revision 01, dated February 12, 2002; 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 A320–53–1027, 

Revision 2, dated June 8, 1995; and Airbus 

Service Bulletin A320–53–1028, dated March 

1, 1994; was approved previously by the 

Director of the Federal Register as of July 14, 

1998 (63 FR 31345, June 9, 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 3: The subject of this AD is addressed 

in French airworthiness directive 2002–

183(B), dated April 3, 2002.

Effective Date 

(h) This amendment becomes effective on 

March 15, 2004.

Issued in Renton, Washington, on January 

30, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2582 Filed 2–6–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–170–AD, Amendment 

39–13467; AD 2004–03–23] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–200 and –300 Series 

Airplanes Equipped With a Main Deck 

Cargo Door Installed in Accordance 

With Supplemental Type Certificate 

(STC) SA2969SO

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to certain Boeing Model 737–

200 and –300 series airplanes, that 

currently requires a one-time inspection 

to detect cracks of the lower frames and 

reinforcing angles of the main deck 

cargo door where the door latch fittings 

attach between certain fuselage stations 

and water lines, and replacement of any 

cracked part with a new part having the 

same part number. This amendment 

continues to require the existing actions 

and corrects a reference to an incorrect 

fuselage station. The actions specified 

by the AD are intended to detect and 

correct cracking of the lower portion of 

the main deck cargo door frames, which 

could result in sudden depressurization, 

loss or opening of the main deck cargo 

door during flight, and loss of control of 

the airplane.

DATES: Effective February 24, 2004. 

The incorporation by reference of a 

certain publication, as listed in the 

regulations, was approved previously by 

the Director of the Federal Register as of 

May 29, 2001 (66 FR 20380, April 23, 

2001). 

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. 2003–NM–

170–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-anmnprmcomment@faa.gov. Comments sent 

via fax or the Internet must contain 

‘‘Docket No. 2003-NM–170-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 for 

Windows or ASCII text. 

The service information referenced in 

the proposed rule may be obtained from 

Pemco World Air Services, 100 Pemco 

Drive, Dothan, AL 36303. This 

information may be examined at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue, SW., Renton, 

Washington; or at the FAA, Atlanta 

Aircraft Certification Office, One Crown 

Center, 1895 Phoenix Boulevard, Suite 

450, Atlanta, Georgia; or at the Office of 

the Federal Register, 800 North Capitol 

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

FOR FURTHER INFORMATION CONTACT: Don 

Buckley, Aerospace Engineer, Airframe 

and Propulsion Branch, ACE–117A, 

FAA, Atlanta Aircraft Certification 

Office, One Crown Center, 1895 Phoenix 

Boulevard, Suite 450, Atlanta, Georgia 

30337–2748, telephone (770) 703–6086; 

fax (770) 703–6097.

SUPPLEMENTARY INFORMATION: On April 

12, 2001, the FAA issued AD 2001–08–

07, amendment 39–12184 (66 FR 20380, 

April 23, 2001), applicable to certain 

Boeing Model 737–200 and –300 series 

airplanes, to require a one-time 

inspection to detect cracks of the lower 

frames and reinforcing angles of the 

main deck cargo door where the door 

latch fittings attach between certain 

fuselage stations and water lines, and 

replacement of any cracked part with a 

new part having the same part number. 

That action was prompted by reports 

that, during the inspections required by 

the existing AD, cracks were found in 

the reinforcing angles of the main deck 

cargo door frame. The requirements of 

that AD are intended to detect and 

correct cracking of the lower portion of 

the main deck cargo door frames, which 

could result in sudden depressurization, 

loss or opening of the main deck cargo 

door during flight, and loss of control of 

the airplane. 

Actions Since Issuance of Previous Rule 

Since the issuance of that AD, several 

commenters point out a typographical 

error in paragraphs (a) and (b) of the AD. 

The first sentence of those paragraphs 

state, ‘‘* * * at the location where the 

door latch fittings attach between 

fuselage station (FS) 361.86 and FS 

298.12 * * *.’’ FS 298.12 is incorrect; 

the correct FS is 498.12, which is 

specified in the service bulletin cited in 

that AD (i.e., Pemco Service Bulletin 

737–52–003, Revision 2, dated 

September 13, 2000, including 

Federal Register / Vol. 69, No. 26 / Monday, February 9, 2004 / Rules and Regulations 5925

Attachment 1, dated August 10, 2000.) 

Because neither of the two airplanes 

affected by this action are on the U.S. 

Register, the public has not acted in 

reliance on the error. Therefore, public 

notice and comment are unnecessary, 

because the public would have no 

interest in commenting. 

Explanation of Requirements of 

Proposed 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 cracking of the lower portion of 

the main deck cargo door frames, which 

could result in sudden depressurization, 

loss or opening of the main deck cargo 

door during flight, and loss of control of 

the airplane. This AD supersedes AD 

2001–08–07 to require the existing onetime inspection to detect cracks of the 

lower frames and reinforcing angles of 

the main deck cargo door where the 

door latch fittings attach between the 

correct fuselage stations and water lines, 

and replacement of any cracked part 

with a new part having the same part 

number. The actions are required to be 

accomplished in accordance with 

Pemco Service Bulletin 737–52–0037, 

Revision 2, dated September 13, 2000, 

including Attachment 1, dated August 

10, 2000, described previously in AD 

2001–08–07.

Cost Impact 

None of the Model 737–200 and –300 

series airplanes equipped with a main 

deck cargo door installed in accordance 

with Supplemental Type Certificate 

SA2969SO 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 500 work hours per 

airplane to accomplish the required 

inspection, at an average labor rate of 

$65 per work hour. Based on these 

figures, the cost impact of the inspection 

required by this AD on U.S. operators is 

estimated to be $32,500 per airplane. 

Should an affected airplane be 

imported and placed on the U.S. 

Register in the future, it would require 

approximately 128 work hours per 

airplane to accomplish the replacement, 

at an average labor rate of $65 per work 

hour. Required parts will cost 

approximately $15,521 per airplane. 

Based on these figures, the cost impact 

of the replacement required by this AD 

on U.S. operators is estimated to be 

$23,841 per airplane. 

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 2003–NM–170–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 

removing amendment 39–12184 (66 FR 

20380, April 23, 2001), and by adding a 

new airworthiness directive (AD), 

amendment 39–13467 to read as follows:

2004–03–23 Boeing: Amendment 39–13467. 

Docket 2003–NM–170–AD. Supersedes 

AD 2001–08–07, Amendment 39–12184.

Applicability: Model 737–200 and –300 

series airplanes, equipped with a main deck 

cargo door installed in accordance with 

5926 Federal Register / Vol. 69, No. 26 / Monday, February 9, 2004 / Rules and Regulations 

Supplemental Type Certificate (STC) 

SA2969SO; certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To detect and correct cracking of the lower 

portion of the main deck cargo door frames, 

which could result in sudden 

depressurization, loss or opening of the main 

deck cargo door during flight, and loss of 

control of the airplane; accomplish the 

following: 

Actions Addressing Door Frames or 

Reinforcing Angles That Have Been 

Replaced 

(a) For airplanes on which any door frame 

or reinforcing angle at the location where the 

door latch fittings attach between fuselage 

station (FS) 361.86 and FS 498.12 and water 

line (WL) 202.35 and WL 213.00 has been 

replaced before the effective date of this AD: 

Do the actions specified in paragraphs (a)(1) 

and (a)(2) of this AD per the Accomplishment 

Instructions of Pemco Service Bulletin 737–

52–0037, Revision 2, dated September 13, 

2000, including Attachment 1, dated August 

10, 2000. 

(1) Within 3,000 flight cycles after 

accomplishment of the replacement, do a 

high frequency eddy current (HFEC) 

inspection to detect cracks of the replaced 

lower frames or replaced reinforcing angles 

of the main deck cargo door, as applicable. 

(i) If no crack is detected, repeat the HFEC 

inspection thereafter at intervals of 1,300 

flight cycles on the replaced part. 

(ii) If any crack is detected, before further 

flight, replace the cracked part with a new 

part having the same part number per the 

service bulletin. Within 3,000 flight cycles 

after accomplishment of the replacement, do 

the HFEC inspection required by paragraph 

(a)(1) of this AD. 

(2) Before or upon the accumulation of 

7,000 total flight cycles on any lower frame 

or reinforcing angle of the main deck cargo 

door, replace the lower frame or reinforcing 

angle, as applicable, with new parts. Within 

3,000 flight cycles after accomplishment of 

the replacement, do the HFEC inspection 

required by paragraph (a)(1) of this AD. 

Actions Addressing Door Frames or 

Reinforcing Angles That Have Not Been 

Replaced 

(b) For airplanes on which any door frame 

or reinforcing angle at the location where the 

door latch fittings attach between FS 361.86 

and FS 498.12 and WL 202.35 and WL 213.00 

has not been replaced before the effective 

date of this AD: Within 1,300 flight cycles 

after accomplishment of the HFEC inspection 

required by AD 2000–17–51, amendment 39–

11877, do the action specified in either 

paragraph (b)(1) or (b)(2) of this AD, as 

applicable, per the Accomplishment 

Instructions of Pemco Service Bulletin 737–

52–0037, Revision 2, dated September 13, 

2000, including Attachment 1, dated August 

10, 2000. 

(1) For airplanes that have accumulated 

less than 7,000 total flight cycles since 

installation of STC SA2969SO: Do an HFEC 

inspection to detect cracks of the lower 

frames and reinforcing angles of the main 

deck cargo door where the door latch fittings 

attach between FS 361.86 and FS 498.12 and 

WL 202.35 and WL 213.00. 

(i) If no crack is detected, do the actions 

specified in paragraphs (b)(1)(i)(A) and 

(b)(1)(i)(B) of this AD. 

(A) Repeat the HFEC inspection thereafter 

at intervals of 1,300 flight cycles on the 

airplane, but not to exceed the accumulation 

of 7,000 total flight cycles on the airplane. 

(B) Before the accumulation of 7,000 total 

flight cycles on the airplane, replace the 

lower frame and reinforcing angle with new 

parts per the service bulletin. Within 3,000 

flight cycles after accomplishment of the 

replacement, do the HFEC inspection 

required by paragraph (a)(1) of this AD. 

(ii) If any crack is detected, before further 

flight, replace the cracked part with a new 

part having the same part number per the 

service bulletin. Within 3,000 flight cycles 

after accomplishment of the replacement, do 

the HFEC inspection required by paragraph 

(a)(1) of this AD. 

(2) For airplanes that have accumulated 

7,000 or more total flight cycles since 

installation of STC SA2969SO: Replace the 

lower frames and reinforcing angles with 

new parts. Within 3,000 flight cycles after 

accomplishment of the replacement, do the 

HFEC inspection required by paragraph (a)(1) 

of this AD. 

Alternative Methods of Compliance 

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

Manager, Atlanta Aircraft Certification Office 

(ACO), FAA, is authorized to approve 

alternative methods of compliance (AMOCs) 

for this AD. 

(2) Alternative methods of compliance, 

approved previously in accordance with AD 

2000–17–51, amendment 39–11877, are 

approved as alternative methods of 

compliance with the initial HFEC inspection 

required by paragraph (a)(1) of this AD. 

Incorporation by Reference 

(d) The actions shall be done in accordance 

with Pemco Service Bulletin 737–52–0037, 

Revision 2, dated September 13, 2000, 

including Attachment 1, dated August 10, 

2000. This incorporation by reference was 

approved previously by the Director of the 

Federal Register as of May 29, 2001 (66 FR 

20380, April 23, 2001). Copies may be 

obtained from Pemco World Air Services, 

100 Pemco Drive, Dothan, AL 36303. Copies 

may be inspected at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue, 

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

Atlanta Aircraft Certification Office, One 

Crown Center, 1895 Phoenix Boulevard, 

Suite 450, Atlanta, Georgia; or at the Office 

of the Federal 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 

30, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2575 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–303–AD; Amendment 

39–13454; AD 2004–03–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

(Collectively Called A300–600) Series 

Airplanes; and Model A310 Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to all Airbus Model A300 

B4–600, B4–600R, and F4–600R 

(collectively called A300–600) series 

airplanes; and Model A310 series 

airplanes. This AD requires revising the 

Airplane Flight Manual (AFM) to 

provide the flight crew with procedures 

to maintain controllability of the 

airplane in the event of an in-flight 

deployment of the thrust reverser. This 

action is necessary to ensure that the 

flight crew is advised of the potential 

hazard associated with an in-flight 

deployment of the thrust reverser, and 

the procedures necessary to address it. 

This action is intended to address the 

identified unsafe condition.

DATES: Effective March 15, 2004.

ADDRESSES: Information pertaining to 

this amendment may be examined at the 

Federal Aviation Administration (FAA), 

Transport Airplane Directorate, Rules 

Docket, 1601 Lind Avenue, SW., 

Renton, Washington.

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) to 

include an airworthiness directive (AD) 

that is applicable to all Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

(collectively called A300–600) series 

airplanes; and Model A310 series 

airplanes; was published in the Federal 

Register on August 9, 2002 (67 FR 

51787). That action proposed to require 

revising the Airplane Flight Manual 

(AFM) to provide the flight crew with 

procedures to maintain controllability of 

the airplane in the event of an in-flight 

deployment of the thrust reverser.