[Federal Register Volume 70, Number 5 (Friday, January 7, 2005)]
[Rules and Regulations]
[Pages 1340-1341]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-160]


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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.

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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, [email protected].

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

[[Page 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

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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]
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