1340 Federal Register / Vol. 70, No. 5 / Friday, January 7, 2005 / Rules and Regulations 

Issued in Renton, Washington, on 

December 27, 2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 05–161 Filed 1–6–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–18601; Directorate 

Identifier 2004–NM–34–AD; Amendment 39–

13933; AD 2005–01–09] 

RIN 2120–AA64

Airworthiness Directives; Boeing 

Model 747–100, –200B, –200F, –200C, 

–100B, –300, –100B SUD, –400, –400D, 

–400F, and 747SR Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 747 series airplanes. This 

AD requires a one-time inspection for 

discrepancies of the frame web and 

inner chords on the forward edge frame 

of the number 5 main entry door cutout, 

and related corrective action. This AD is 

prompted by a report of cracking of the 

frame web and inner chords on the 

forward edge frame of the number 5 

main entry door. We are issuing this AD 

to find and fix discrepancies of the 

frame web and inner chords, which 

could result in cracking, subsequent 

severing of the frame, and consequent 

rapid depressurization of the airplane.

DATES: This AD becomes effective 

February 11, 2005. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of February 11, 2005.

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, PO Box 3707, 

Seattle, Washington 98124–2207. You 

can examine this information 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.

You can examine the contents of this 

AD docket on the Internet at http://

dms.dot.gov, or at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., room PL–401, on the plaza level of 

the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT: 

Technical information: Ivan Li, 

Aerospace Engineer, Airframe Branch, 

ANM–120S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056; 

telephone (425) 917–6437; fax (425) 

917–6590. 

Plain language information: Marcia 

Walters, marcia.walters@faa.gov.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR Part 39 with 

an AD for certain Boeing Model 747 

series airplanes. That action, published 

in the Federal Register on July 15, 2004 

(69 FR 42365), proposed to require a 

one-time inspection for discrepancies of 

the frame web and inner chords on the 

forward edge frame of the number 5 

main entry door cutout, and related 

corrective action. 

Examining the Docket 

The AD docket contains the proposed 

AD, comments, and any final 

disposition. You can examine the AD 

docket on the Internet at http://

dms.dot.gov, or in person at the Docket 

Management Facility office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The 

Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the DOT street address stated in the 

ADDRESSES section. 

Comment 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the single comment that has 

been submitted on the proposed AD. 

Request To Change Paragraph (g) 

The commenter (the manufacturer) 

asks that paragraph (g) of the proposed 

AD be changed to read ‘‘For those 

airplanes on which the repetitive 

inspections required by AD 2001–16–

02, amendment 39–12370, have been 

done as of the effective date of this AD, 

no further action is required.’’ The 

commenter states that the inspection 

required by AD 2001–16–02 (referenced 

as a related AD in the proposed AD) is 

a surface eddy current inspection and is 

more intensive than the detailed 

inspection specified in the proposed 

AD. The commenter notes that the 

repetitive inspections in AD 2001–16–

02 adequately detect any cracking prior 

to loss of residual strength of the chord. 

The commenter adds that a nick or 

gouge does not affect the crack growth 

rate, so the safety concern in the 

proposed AD is addressed by the 

repetitive inspections. 

We agree with the commenter. The 

repetitive inspections for cracking 

required by AD 2001–16–02 are more 

extensive than the one-time inspection 

required by this AD, and must be 

repeated at intervals not to exceed 3,000 

flight cycles. Initiating those inspections 

will find cracking before it reaches 

critical length; therefore, the one-time 

inspection required by this AD is not 

necessary if the repetitive inspections 

are currently being done. For airplanes 

that are at or near the 10,000-flight-cycle 

threshold, and have not been inspected 

per AD 2001–16–02, the purpose of this 

AD is to close the gap between the 

compliance time for the initial 

inspection required by AD 2001–16–02 

(before the accumulation of 16,000 total 

flight cycles) and the one-time 

inspection required by this AD. The AD 

requires that operators inspect the 

airplane at or before 10,000 total flight 

cycles, or within the specified grace 

period. Therefore, paragraph (g) of this 

AD has been changed to specify that 

operators currently accomplishing the 

repetitive inspections required by AD 

2001–16–02 are not required to 

accomplish the one-time inspection 

required by this AD. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

that has 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. 

Costs of Compliance 

There are about 1,055 airplanes 

worldwide of the affected design, this 

AD affects about 220 airplanes of U.S. 

registry. The inspection takes about 2 

work hours per airplane, at an average 

labor rate of $65 per work hour. Based 

on these figures, the estimated cost of 

the inspection required by this AD for 

U.S. operators is $28,600, or $130 per 

airplane. 

Authority for This Rulemaking 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the United States Code. 

Subtitle I, Section 106, describes the 

authority of the FAA Administrator. 

Subtitle VII, Aviation Programs, 

describes in more detail the scope of the 

agency’s authority. 

This rulemaking is promulgated 

under the authority described in 

Federal Register / Vol. 70, No. 5 / Friday, January 7, 2005 / Rules and Regulations 1341

Subtitle VII, Part A, Subpart III, Section 

44701, ‘‘General requirements.’’ Under 

that section, Congress charges the FAA 

with promoting safe flight of civil 

aircraft in air commerce by prescribing 

regulations for practices, methods, and 

procedures the Administrator finds 

necessary for safety in air commerce. 

This regulation is within the scope of 

that authority because it addresses an 

unsafe condition that is likely to exist or 

develop on products identified in this 

AD.

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD 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. 

For the reasons discussed above, I 

certify that this AD: 

(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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD. See the ADDRESSES section for 

a location to examine the regulatory 

evaluation.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD):

2005–01–09 Boeing: Amendment 39–13933. 

Docket No. FAA–2004–18601; 

Directorate Identifier 2004–NM–34–AD. 

Effective Date 

(a) This AD becomes effective February 11, 

2005. 

Affected ADs 

(b) Accomplishing this AD will not 

terminate the repetitive inspections required 

by AD 2001–16–02, amendment 39–12370. 

Applicability 

(c) This AD applies to Boeing Model 747–

100, –200B, –200F, –200C, –100B, –300, 

–100B SUD, –400, –400D, –400F, and 747SR 

series airplanes; line numbers 1 through 1333 

inclusive; certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by a report of 

cracking of the frame web and inner cords on 

the forward edge frame of the number 5 main 

entry door. We are issuing this AD to find 

and fix discrepancies of the frame web and 

inner cords, which could result in cracking, 

subsequent severing of the frame, and 

consequent rapid depressurization of the 

airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

One-Time Inspection 

(f) For airplanes on which the repetitive 

inspections required by AD 2001–16–02 have 

not been accomplished as of the effective 

date of this AD: Do a one-time detailed 

inspection for discrepancies (nicks, 

scratches, and/or gouges) of the frame web 

and inner cords (forward and aft) of the 

forward edge frame of the number 5 main 

entry door cutout, by doing all the applicable 

actions specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2494, dated September 18, 2003. Do 

the inspection at the latest of the times 

specified in paragraphs (f)(1), (f)(2), and (f)(3) 

of this AD. 

(1) Before the accumulation of 10,000 total 

flight cycles. 

(2) Within 1,500 flight cycles after the 

effective date of this AD. 

(3) Within 24 months after the effective 

date of this AD. 

(g) For airplanes on which the repetitive 

inspections required by AD 2001–16–02 have 

been accomplished as of the effective date of 

this AD: No further action is required by this 

AD.

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive visual 

examination of a specific structural area, 

system, installation, or assembly to detect 

damage, failure, or irregularity. Available 

lighting is normally supplemented with a 

direct source of good lighting at intensity 

deemed appropriate by the inspector. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be used. Surface cleaning 

and elaborate access procedures may be 

required.’’

Related Corrective Action 

(h) If any discrepancy is found during the 

inspection required by paragraph (f) of this 

AD: Before further flight, do all the related 

corrective actions specified in the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2494, dated 

September 18, 2003. Where the service 

bulletin specifies contacting the 

manufacturer for disposition of certain repair 

conditions, repair before further flight per a 

method approved by the Manager, Seattle 

Aircraft Certification Office (ACO), FAA; or 

per data meeting the type certification basis 

of the airplane approved by a Boeing 

Company Designated Engineering 

Representative who has been authorized by 

the Manager, Seattle ACO, to make such 

findings. For a repair method to be approved, 

the approval must specifically refer to this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Seattle ACO, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by a 

Boeing Company Designated Engineering 

Representative who has been authorized by 

the Manager, Seattle ACO, to make those 

findings. For a repair method to be approved, 

the approval must specifically refer to this 

AD. 

Material Incorporated by Reference 

(j) You must use Boeing Alert Service 

Bulletin 747–53A2494, dated September 18, 

2003, to perform the actions that are required 

by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approves the incorporation by 

reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. For 

copies of the service information, contact 

Boeing Commercial Airplanes, PO Box 3707, 

Seattle, Washington 98124–2207. For 

information on the availability of this 

material at the National Archives and 

Records Administration (NARA), call (202) 

741–6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html. You may view the AD 

docket at the Docket Management Facility, 

Department of Transportation, 400 Seventh 

Street SW., room PL–401, Nassif Building, 

Washington, DC.

Issued in Renton, Washington, on 

December 27, 2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 05–160 Filed 1–6–05; 8:45 am] 

BILLING CODE 4910–13–P