Federal Register / Vol. 68, No. 176 / Thursday, September 11, 2003 / Rules and Regulations 53503

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:

2003–18–06 Airbus: Amendment 39–13297. 

Docket 2000–NM–411–AD.

Applicability: Model A319–131 and –132; 

A320–231, –232, and –233; and A321–131 

and –231 series airplanes; certificated in any 

category; except those airplanes on which the 

following have been incorporated: Airbus 

Modifications 21948/P6222 and 30869 in 

production; Airbus Modifications 24259/

P6222 and 30869 in production; Airbus 

Modifications 24259/P6222 and 24259/P6473 

in production; or Airbus Service Bulletin 

A320–71–1028, dated March 23, 2001, inservice.

Note 1: This AD applies to each airplane 

identified in the preceding applicability 

provision, regardless of whether it has been 

otherwise modified, altered, or repaired in 

the area subject to the requirements of this 

AD. For airplanes that have been modified, 

altered, or repaired so that the performance 

of the requirements of this AD is affected, the 

owner/operator must request approval for an 

alternative method of compliance in 

accordance with paragraph (b) of this AD. 

The request should include an assessment of 

the effect of the modification, alteration, or 

repair on the unsafe condition addressed by 

this AD; and, if the unsafe condition has not 

been eliminated, the request should include 

specific proposed actions to address it.

Compliance: Required as indicated, unless 

accomplished previously.

To prevent separation of the engine fan 

cowl door from the airplane in flight, which 

could result in damage to the airplane and 

hazards to persons or property on the ground, 

accomplish the following: 

Modification and/or Installation 

(a) Within 18 months after the effective 

date of this AD, do the action(s) specified in 

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

applicable. 

(1) For Configuration 01 airplanes 

identified in Airbus Service Bulletin A320–

71–1028, dated March 23, 2001: Modify the 

door latches of the fan cowl of both engines 

(i.e., installation of new anti-swivel plates 

and weights), and install a new hold-open 

device, per the service bulletin. 

(2) For Configuration 02 airplanes 

identified in Airbus Service Bulletin A320–

71–1028, dated March 23, 2001: Install a new 

hold-open device per the service bulletin.

Note 2: Airbus Service Bulletin A320–71–

1028 refers to International Aero Engines 

Service Bulletin V2500–NAC–71–0256, dated 

June 23, 1999, as an additional source of 

service information for accomplishment of 

the required actions. International Aero 

Engines Service Bulletin V2500–NAC–71–

0256 recommends that International Aero 

Engines Service Bulletin V2500–NAC–71–

0227 be accomplished concurrently. This AD 

does not require accomplishment of 

International Aero Engines Service Bulletin 

V2500-NAC–71–0227.

Alternative Method of Compliance 

(b) An alternative method of compliance or 

adjustment of the compliance time that 

provides an acceptable level of safety may be 

used if approved by the Manager, 

International Branch, ANM–116, FAA. 

Operators shall submit their requests through 

an appropriate FAA Principal Maintenance 

Inspector, who may add comments and then 

send it to the Manager, International Branch, 

ANM–116.

Note 3: Information concerning the 

existence of approved alternative methods of 

compliance with this AD, if any, may be 

obtained from the International Branch, 

ANM–116.

Special Flight Permits 

(c) Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the requirements of this AD 

can be accomplished. 

Incorporation by Reference 

(d) The actions shall be done in accordance 

with Airbus Service Bulletin A320–71–1028, 

dated March 23, 2001. 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 Industrie, 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 4: The subject of this AD is addressed 

in French airworthiness directive 2001–

381(B), dated September 5, 2001.

Effective Date 

(e) This amendment becomes effective on 

October 16, 2003.

Issued in Renton, Washington, on August 

29, 2003. 

Vi L. Lipski, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 03–22705 Filed 9–10–03; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2001–NM–240–AD; Amendment 

39–13301; AD 2003–18–10] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 767–200, –300, –300F, and 

–400ER Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to certain Boeing Model 767 

series airplanes, that currently requires 

revising the Airworthiness Limitations 

Section of the Maintenance Planning 

Data (MPD) Document (767 

Airworthiness Limitations Instructions 

(ALI)). The revision incorporates into 

the ALI certain inspections and 

compliance times to detect fatigue 

cracking of principal structural elements 

(PSE). This amendment expands the 

applicability in the existing AD, and 

requires incorporating a new revision 

into the Airworthiness Limitations 

Section of the MPD Document. The 

actions specified by this AD are 

intended to ensure that fatigue cracking 

of various PSEs is detected and 

corrected; such fatigue cracking could 

adversely affect the structural integrity 

of these airplanes. This action is 

intended to address the identified 

unsafe condition.

DATES: Effective October 16, 2003. 

The incorporation by reference of 

Appendix B of Boeing 767 Maintenance 

Planning Data Document D622T001, 

Revision December 2002; Subsection B, 

Section 9, of Boeing 767 Maintenance 

Planning Data Document D622T001–9, 

Revision June 2000; Subsection B, 

Section 9, of Boeing 767 Maintenance 

Planning Data Document D622T001–9, 

Revision February 2001; and Subsection 

B, Section 9, of Boeing 767 Maintenance 

Planning Data Document D622T001–9, 

Revision October 2002; is approved by 

the Director of the Federal Register as of 

October 16, 2003. 

The incorporation by reference of 

Subsection B of Boeing 767 

53504 Federal Register / Vol. 68, No. 176 / Thursday, September 11, 2003 / Rules and Regulations 

Maintenance Planning Data Document 

D622T001–9, Revision June 1997, as 

listed in the regulations, was approved 

previously by the Director of the Federal 

Register as of June 1, 2001 (66 FR 21077, 

April 27, 2001).

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Boeing Commercial Airplane 

Group, P.O. Box 3707, Seattle, 

Washington 98124–2207. 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:

Suzanne Masterson, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6441; fax (425) 917–6590.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 2001–08–28, 

amendment 39–12205 (66 FR 21077, 

April 27, 2001), which is applicable to 

certain Boeing Model 767 series 

airplanes, was published in the Federal 

Register on March 3, 2003 (68 FR 9951). 

The action proposed to continue to 

require revising the Airworthiness 

Limitations Section of the Maintenance 

Planning Data (MPD) Document (767 

Airworthiness Limitations Instructions 

(ALI)). The revision incorporates into 

the ALI certain inspections and 

compliance times to detect fatigue 

cracking of principal structural elements 

(PSE). The action also proposed to 

expand the applicability in the existing 

AD, and incorporate a new revision into 

the Airworthiness Limitations Section 

of the MPD Document. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

comments received. 

One commenter has no issues with 

the proposed AD and is in the process 

of incorporating the actions into its 

Model 767 maintenance program. 

Request for Certain Clarification of 

Certain Paragraphs 

One commenter notes that the 

requirements of AD 2001–08–28 are 

restated in paragraphs (a) and (b) of the 

proposed AD, and the new requirements 

are stated in paragraphs (c) and (d) of 

the proposed AD. The commenter states 

that, since the intent of the proposed AD 

is for operators to incorporate the new 

requirements, paragraphs (c) and (d) 

should be clarified to specify that 

accomplishment of those paragraphs 

terminates the requirements specified in 

paragraphs (a) and (b). We agree with 

the commenter; however, paragraph (b) 

merely specifies that no alternative 

inspections or inspection intervals shall 

be approved unless an alternative 

method of compliance (AMOC) is 

approved, it does not contain any 

requirements. Therefore, paragraph (c) 

of this final rule has been changed for 

clarification to include the statement 

that accomplishment of paragraph (c) 

terminates the requirements in 

paragraph (a) of this AD. 

Another commenter asks that 

paragraph (c) of the proposed AD be 

changed to clarify that Appendix B is 

part of Boeing Document D622T001, not 

D622T001–9. The commenter states that 

the current wording incorrectly 

specifies that Appendix B is part of 

Boeing Document D622T001–9. We 

agree with the commenter and have 

changed paragraph (c) of this final rule 

for clarification. 

Request To Delete Paragraph (e)(3) 

One commenter states that there has 

been no change to any airworthiness 

limitation inspection in the June 2000 

revision of the MPD, so that revision is 

still a valid AMOC for the new 

requirements specified in the proposed 

AD. Therefore, the commenter suggests 

that paragraph (e)(3) of the proposed 

AD; which specifies that the procedures 

in Subsection B of Boeing Document 

D622T001–9, Revision June 2000, are 

not approved as AMOCs with paragraph 

(d) of this AD; be deleted. 

We agree with the commenter. We 

have reviewed Revisions June 2000, 

February 2001, and October 2002, and 

find the only change to Subsection B, 

Section 9, is the language describing the 

requirement to reduce inspection 

intervals to match those in Section 8, 

once the inspection threshold is 

reached. All revisions contain the same 

inspections and are acceptable to use for 

accomplishment of the actions required. 

Therefore, we have deleted paragraph 

(e)(3) of this final rule, as well as the 

reference to paragraph (e)(3) that was 

specified in paragraph (e)(2) of the 

proposed AD. 

Request To Change Applicability 

One commenter, the manufacturer, 

asks that the Model 767–400 series be 

removed from the applicability 

specified in the proposed AD. The 

commenter states that the Model 767–

400 is not an ‘‘official’’ type-certificated 

minor model, and the type certificate 

data sheet (TCDS) lists only the Model 

767–400ER series. We agree with the 

commenter; as the TCDS specifies only 

the Model 767–400ER series, we have 

removed all references to the Model 

767–400 series from this final rule 

accordingly. 

Request To Change Compliance Time 

One commenter states that the 

compliance time in the existing AD was 

three years from June 1, 2001, as 

specified in paragraph (a) of the 

proposed AD, whereas the compliance 

time in the new requirements, as 

specified in paragraph (c) of the 

proposed AD, is within 18 months after 

the effective date of the AD. The 

commenter asks that the compliance 

time for paragraphs (a) and (c) of the 

proposed AD be changed to allow one 

of two options. Option 1—The 

compliance time should be three years 

from the release date of the AD. Option 

2—The compliance time should be three 

years from the release date of the AD for 

airplanes having line numbers 670 

through 895 inclusive, and 18 months 

from the release date of the AD for 

airplanes having line numbers 1 through 

669 inclusive. The commenter states 

that this will give operators more 

flexibility, while retaining the intent of 

the existing AD. 

We do not agree with the commenter. 

The commenter provides no technical 

justification for changing the 

compliance time as requested. A 

compliance time of 18 months, rather 

than 3 years, for incorporating the latest 

revision of Subsection B, Section 9, of 

Boeing MPD Document D622T001–9 

will ensure the continued safety of aging 

airplanes. In developing an appropriate 

compliance time for the actions required 

by this AD, the FAA considered not 

only the safety issues, but the 

manufacturer’s recommendations, parts 

availability, and the practical aspect of 

accomplishing the required actions 

within an interval paralleling normal 

scheduled maintenance for the majority 

of affected operators. In light of all of 

these factors, the FAA considers 18 

months an appropriate compliance time 

wherein safety will not be adversely 

affected. No change to the final rule is 

necessary in this regard. 

Request To Remove New Revisions to 

MPD 

One commenter asks that Revisions 

June 2000, February 2001, and October 

2002 to Subsection B, Section 9, of 

Boeing Document D622T001–9 of the 

MPD be removed from paragraph (a) of 

the proposed AD. The commenter states 

that the existing AD only referenced 

Federal Register / Vol. 68, No. 176 / Thursday, September 11, 2003 / Rules and Regulations 53505

Revision June 1997, and did not include 

the other revision levels specified in 

paragraph (a) of the proposed AD. The 

commenter adds that the other revisions 

may be approved as AMOCs for the 

existing AD.

We do not agree with the commenter. 

The revisions that have been added to 

paragraph (a) of this AD are alternate 

revisions that have been previously 

approved as AMOCs for the 

requirements in paragraph (a) of this 

AD, and are acceptable to use for 

accomplishment of the actions required. 

In addition, AMOCs have been granted 

for inspections of individual repairs and 

alterations that interfered with the 

inspections specified in Section 9 of 

Boeing MPD Document D622T001–9. 

The intent of paragraph (e)(2) of this 

final rule is to allow operators to 

continue to use those AMOCs for the 

accomplishment of the inspections in 

this final rule. No change to the final 

rule is necessary in this regard. 

Changes to 14 CFR Part 39 

On July 10, 2002, the FAA issued a 

new version of 14 CFR part 39 (67 FR 

47997, July 22, 2002), which governs the 

FAAs airworthiness directives system. 

The regulation now includes material 

that relates to altered products, special 

flight permits, and AMOCs. However, 

for clarity and consistency in this final 

rule, we have retained the language of 

the NPRM regarding that material. 

Conclusion 

After careful review of the available 

data, including the comments noted 

above, the FAA has determined that air 

safety and the public interest require the 

adoption of the rule with the changes 

previously described. The FAA has 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Cost Impact 

There are approximately 884 

airplanes of the affected design in the 

worldwide fleet. We estimate that 393 

airplanes of U.S. registry will be affected 

by this AD. 

The actions that are currently 

required by AD 2001–08–28 take 

approximately 1 work hour per airplane 

to accomplish, at an average labor rate 

of $60 per work hour. Based on these 

figures, the cost impact of the currently 

required actions is estimated to be $60 

per airplane. 

The new actions that are required by 

this AD action will take approximately 

1 work hour per airplane to accomplish, 

at an average labor rate of $60 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 

$23,580, or $60 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 

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 39–12205 (66 FR 

21077, April 27, 2001), and by adding a 

new airworthiness directive (AD), 

amendment 39–13301, to read as 

follows:

2003–18–10 Boeing: Amendment 39–13301. 

Docket 2001–NM–240–AD. Supersedes 

AD 2001–08–28, Amendment 39–12205.

Applicability: Model 767–200, –300, 

–300F, and –400ER series airplanes having 

line numbers 1 through 895 inclusive, 

certificated in any category.

Note 1: This AD applies to each airplane 

identified in the preceding applicability 

provision, regardless of whether it has been 

modified, altered, or repaired in the area 

subject to the requirements of this AD. For 

airplanes that have been modified, altered, or 

repaired so that the performance of the 

requirements of this AD is affected, the 

owner/operator must request approval for an 

alternative method of compliance in 

accordance with paragraph (e)(1) of this AD. 

The request should include an assessment of 

the effect of the modification, alteration, or 

repair on the unsafe condition addressed by 

this AD; and, if the unsafe condition has not 

been eliminated, the request should include 

specific proposed actions to address it.

Compliance: Required as indicated, unless 

accomplished previously. 

To ensure that fatigue cracking of various 

principal structural elements, which could 

adversely affect the structural integrity of 

these airplanes, is detected and corrected, 

accomplish the following: 

Restatement of Requirements of AD 2001–

08–28 

Revise Section 9 of the Boeing 767 

Maintenance Planning Data (MPD) Document 

(a) For Model 767–200 and –300 series 

airplanes having line numbers 1 through 669 

inclusive: Within 3 years after June 1, 2001 

(the effective date of AD 2001–08–28, 

amendment 39–12205), revise Subsection B, 

Section 9, of Boeing 767 MPD Document 

D622T001–9, entitled ‘‘Airworthiness 

Limitations and Certification Maintenance 

Requirements,’’ to incorporate Revision June 

1997, June 2000, February 2001, or October 

2002.

Note 2: The referenced Subsection B 

contains a requirement that cracks found 

during the specified inspections be reported 

to the Seattle Aircraft Certification Office 

(ACO), FAA. Information collection 

requirements contained in this regulation 

have been approved by the Office of 

Management and Budget under the 

provisions of the Paperwork Reduction Act of 

1980 (44 U.S.C. 3501, et seq.) and have been 

assigned OMB Control Number 2120–0056.

Note 3: For the purposes of this AD, the 

terms principal structural elements (PSEs) as 

used in this AD, and structural significant 

items (SSIs) as used in Section 9 of Model 

767 MPD Document, are considered to be 

interchangeable.

53506 Federal Register / Vol. 68, No. 176 / Thursday, September 11, 2003 / Rules and Regulations 

Alternative Inspections and Inspection 

Intervals 

(b) Except as provided by paragraph (e)(1) 

of this AD: After the actions required by 

paragraph (a) of this AD have been 

accomplished, no alternative inspections or 

inspection intervals shall be approved for the 

SSIs contained in Section 9 of Boeing 767 

MPD Document D622T001–9, Revision June 

1997, June 2000, or February 2001. 

New Requirements of This AD 

Revise Section 9 of the Boeing 767 MPD 

(c) For Model 767–200, –300, –300F, and 

–400ER series airplanes having line numbers 

1 through 895 inclusive: Within 18 months 

after the effective date of this AD, revise 

Subsection B, Section 9, of Boeing 767 MPD 

Document D622T001–9, entitled 

‘‘Airworthiness Limitations and Certification 

Maintenance Requirements,’’ to incorporate 

Revision October 2002; and Appendix B of 

Boeing 767 MPD Document D622T001, 

Revision December 2002. Accomplishment of 

this paragraph terminates the requirements in 

paragraph (a) of this AD. 

Alternative Inspections and Inspection 

Intervals 

(d) Except as provided by paragraph (e)(1) 

of this AD: After the actions required by 

paragraph (c) of this AD have been 

accomplished, no alternative inspections or 

inspection intervals shall be approved for the 

SSIs contained in Section 9 of Boeing 767 

MPD Document D622T001–9, Revision 

October 2002. 

Alternative Methods of Compliance 

(e)(1) An alternative method of compliance 

or adjustment of the compliance time that 

provides an acceptable level of safety may be 

used if approved by the Manager, Seattle 

ACO. Operators shall submit their requests 

through an appropriate FAA Principal 

Maintenance Inspector, who may add 

comments and then send it to the Manager, 

Seattle ACO. 

(2) Alternative methods of compliance, 

approved previously in accordance with AD 

2001–08–28, amendment 39–12205, are 

approved as alternative methods of 

compliance with paragraphs (a) and (c) of 

this AD.

Note 4: Information concerning the 

existence of approved alternative methods of 

compliance with this AD, if any, may be 

obtained from the Seattle ACO.

Special Flight Permits 

(f) Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the requirements of this AD 

can be accomplished. 

Incorporation by Reference 

(g) The actions shall be done in accordance 

with the applicable documents listed in 

Table 1 of this AD, as follows:

TABLE 1.—SERVICE DOCUMENTS

Document Page numbers Revision 

Appendix B of Boeing 767, Maintenance Planning Data Document D622T001.Forward, Pages A–N ....................................... December 2002. 

Subsection B of Boeing 767 Maintenance Planning Data Document D622T001–9.List of Effective Pages, Page 9.0–5 ................ June 1997. 

Subsection B, Section 9, of Boeing 767, Maintenance Planning Data Document 

D622T001–9.

List of Effective Pages, Page 9.0–6 ................ June 2000. 

Subsection B, Section 9, of Boeing 767 Maintenance Planning Data Document D622T001–9.List of Effective Pages, Page 9.0–6 ................ February 2001. 

Subsection B, Section 9, of Boeing 767 Maintenance Planning Data Document D622T001–9.List of Effective Pages, Page 9.0–7 ................ October 2002. 

(1) The incorporation by reference of 

Appendix B of Boeing 767 Maintenance 

Planning Data Document D622T001, Revision 

December 2002; Subsection B, Section 9, of 

Boeing 767 Maintenance Planning Data 

Document D622T001–9, Revision June 2000; 

Subsection B, Section 9, of Boeing 767 

Maintenance Planning Data Document 

D622T001–9, Revision February 2001; and 

Subsection B, Section 9, of Boeing 767 

Maintenance Planning Data Document 

D622T001–9, Revision October 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 

Subsection B of Boeing 767 Maintenance 

Planning Data Document D622T001–9, 

Revision June 1997, was approved previously 

by the Director of the Federal Register as of 

June 1, 2001 (66 FR 21077, April 27, 2001). 

(3) Copies may be obtained from Boeing 

Commercial Airplane Group, 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 

Register, 800 North Capitol Street, NW., suite 

700, Washington, DC. 

Effective Date 

(h) This amendment becomes effective on 

October 16, 2003.

Issued in Renton, Washington, on 

September 4, 2003. 

Ali Bahrami, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 03–22990 Filed 9–10–03; 8:45 am] 

BILLING CODE 4910–13–P

SOCIAL SECURITY ADMINISTRATION

20 CFR Part 416 

RIN 0960–AF43 

Access to Information Held by 

Financial Institutions

AGENCY: Social Security Administration.

ACTION: Final rule.

SUMMARY: We are revising our 

regulations to implement a law that will 

enhance our access to financial account 

information of Supplemental Security 

Income (SSI) applicants and recipients 

and other individuals whose income 

and resources we consider as being 

available to the applicant or recipient.

EFFECTIVE DATE: These regulations are 

effective October 14, 2003.

FOR FURTHER INFORMATION CONTACT:

Martin Sussman, Regulations Officer, 

Office of Regulations, 100 Altmeyer 

Building, Social Security 

Administration, 6401 Security 

Boulevard, Baltimore, MD 21235–6401, 

regulations@ssa.gov, (410) 965–1767 or 

TTY (410) 966–5609 for information 

about these rules. For information on 

eligibility or claiming benefits, call our 

national toll-free numbers, 1–800–772–

1213 or TTY 1–800–325–0778 or visit 

our Internet Web site, Social Security 

Online, at http://

www.socialsecurity.gov/. 

Electronic Version: The electronic file 

of this document is available on the date 

of publication in the Federal Register

on the Internet site for the Government 

Printing Office: http://

www.access.gpo.gov/su_docs/aces/

aces140.html. It is also available on our 

Internet site, Social Security Online: 

http://www.socialsecurity.gov/

regulations.

SUPPLEMENTARY INFORMATION: