AD 2005-05-08

[Federal Register Volume 70, Number 47 (Friday, March 11, 2005)]
[Rules and Regulations]
[Pages 12113-12115]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 05-4410]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19470; Directorate Identifier 2003-NM-268-AD; 
Amendment 39-13997; AD 2005-05-08]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100B SUD, -300, -400, 
and -400D Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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[[Page 12114]]

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Boeing Model 747-100B SUD, -300, -400, and -400D series 
airplanes. This AD requires a one-time inspection for discrepancies of 
the fuselage frame to tension tie joints at body stations (BS) 1120 
through 1220 and to determine if steel splice plates are installed on 
the fuselage frames, and related investigative and corrective actions. 
This AD is prompted by reports indicating that severed tension ties 
were found at the fuselage frame joints at BS 1120 and 1140. We are 
issuing this AD to prevent fatigue cracking of the fuselage frame to 
tension tie joints, which could result in severing of the tension ties 
and consequent rapid decompression of the airplane fuselage.

DATES: This AD becomes effective April 15, 2005.
    The incorporation by reference of a certain publication listed in 
the AD is approved by the Director of the Federal Register as of April 
15, 2005.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
    Docket: The AD docket contains the proposed AD, comments, and any 
final disposition. You can examine the AD docket on the Internet at 
<a href="http://dms.dot.gov">http://dms.dot.gov</a>, 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 U.S. 
Department of Transportation, 400 Seventh Street SW., room PL-401, 
Washington, DC. This docket number is FAA-2004-19470; the directorate 
identifier for this docket is 2003-NM-268-AD.

FOR FURTHER INFORMATION CONTACT: 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.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with an AD for certain Boeing Model 747-100B SUD, -300, -400, and -400D 
series airplanes. That action, published in the Federal Register on 
October 29, 2004 (69 FR 63106), proposed to require a one-time 
inspection for discrepancies of the fuselage frame to tension tie 
joints at body stations (BS) 1120 through 1220 and to determine if 
steel splice plates are installed on the fuselage frames, and related 
investigative and corrective actions.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment that has been 
submitted on the proposed AD. The commenter supports the proposed AD.

Changes to Delegation Authority

    Boeing has received a Delegation Option Authorization (DOA). We 
have revised this final rule to delegate the authority to approve an 
alternative method of compliance for any repair required by this AD to 
the Authorized Representative for the Boeing DOA Organization rather 
than the Designated Engineering Representative (DER).

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 as proposed, with the 
change described previously.

Costs of Compliance

    There are about 537 airplanes of the affected design in the 
worldwide fleet. This AD will affect about 67 airplanes of U.S. 
registry. The inspection will take 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 AD for U.S. operators is $8,710, or $130 per 
airplane.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. 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.
    We are issuing this rulemaking under the authority described in 
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 
rulemaking action.

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):

2005-05-08 Boeing: Amendment 39-13997. Docket No. FAA-2004-19470; 
Directorate Identifier 2003-NM-268-AD.

Effective Date

    (a) This AD becomes effective April 15, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model 747-100B SUD, -300, -400, and -400D 
series airplanes; certificated in any category; as identified in 
Boeing Special Attention Service Bulletin 747-53-2483, Revision 1, 
dated August 28, 2003.

Unsafe Condition

    (d) This AD was prompted by reports indicating that severed 
tension ties were found at the fuselage frame joints at body 
stations (BS) 1120 and 1140. We are issuing this AD to prevent 
fatigue cracking of the fuselage frame to tension tie joints, which 
could result in severing of the tension ties

[[Page 12115]]

and consequent rapid decompression of the airplane fuselage.

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/Investigative and Corrective Actions

    (f) Before the accumulation of 4,000 total flight cycles, or 
within 1,000 flight cycles after the effective date of this AD, 
whichever is later: Perform a detailed inspection for discrepancies 
of the fuselage frame to tension tie joints at BS 1120 through BS 
1220, and to determine if steel splice plates are installed on the 
fuselage frames. Do the inspection in accordance with the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2483, Revision 1, dated August 28, 2003. Do any 
applicable investigative and corrective actions before further 
flight in accordance with the service bulletin, except as provided 
by paragraph (h) of 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.''

Determining Number of Flight Cycles for Compliance Time

    (g) For the purposes of calculating the compliance threshold for 
the actions required by paragraph (f) of this AD, all pressurized 
flight cycles, including the number of flight cycles in which cabin 
differential pressure is at 2.0 pounds per square inch (psi) or 
less, must be counted when determining the number of flight cycles 
that have occurred on the airplane. Where the service bulletin and 
this AD differ, the AD prevails.

Repair Requirements

    (h) For any repairs outside the limits of Boeing Special 
Attention Service Bulletin 747-53-2483, Revision 1, dated August 28, 
2003, or if any aluminum splice plate is installed on the fuselage 
frames: Before further flight, repair or replace, as applicable, in 
accordance with a method approved by the Manager, Seattle Aircraft 
Certification Office (ACO), FAA; or in accordance with data meeting 
the certification basis of the airplane approved by an Authorized 
Representative for the Boeing Delegation Option Authorization 
Organization who has been authorized by the Manager, Seattle ACO, to 
make those findings. For a repair or replacement method to be 
approved, as required by this paragraph, the approval must 
specifically refer to this AD.

Actions Accomplished Per Previous Issue of Service Bulletin

    (i) Inspections and corrective actions accomplished before the 
effective date of this AD in accordance with Boeing Special 
Attention Service Bulletin 747-53-2483, dated October 24, 2002, are 
considered acceptable for compliance with the corresponding actions 
specified in this AD.

No Reporting Requirements

    (j) Although the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2483, Revision 1, dated August 28, 
2003; describe procedures for submitting certain information to the 
manufacturer, this AD does not require that action.

Alternative Methods of Compliance (AMOCs)

    (k)(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 an 
Authorized Representative for the Boeing Delegation Option 
Authorization Organization who has been authorized by the Manager, 
Seattle ACO, to make those findings. For a repair method to be 
approved, the repair must meet the certification basis of the 
airplane, and the approval must specifically refer to this AD.

Material Incorporated by Reference

    (l) You must use Boeing Special Attention Service Bulletin 747-
53-2483, Revision 1, dated August 28, 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, P.O. 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 <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>. You may view the AD docket at the 
Docket Management Facility, U.S. Department of Transportation, 400 
Seventh Street SW., room PL-401, Nassif Building, Washington, DC.

    Issued in Renton, Washington, on February 28, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-4410 Filed 3-10-05; 8:45 am]
BILLING CODE 4910-13-P