[Federal Register Volume 71, Number 46 (Thursday, March 9, 2006)]
[Rules and Regulations]
[Pages 12122-12124]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-2142]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23196; Directorate Identifier 2005-NM-187-AD; 
Amendment 39-14506; AD 2006-05-09]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-200C, -200F, -400, -
400D, and -400F Series Airplanes

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

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Boeing Model 747-200C, -200F, -400, -400D, and -400F series 
airplanes. This AD requires repetitive inspections for cracks in the 
overlapping (upper) skin, upper fastener row of the lap joints of the 
fuselage skin in sections 41, 42, and 46; and related investigative and 
corrective actions, if necessary. This AD results from fatigue tests 
and an analysis that identified areas of the fuselage lap joints where 
fatigue cracks can occur. We are issuing this AD to detect and correct 
fatigue cracks in the overlapping (upper) skin, upper fastener row of 
the lap joints of the fuselage skin in sections 41, 42, and 46, which 
could adversely

[[Page 12123]]

affect the structural integrity of the airplane.

DATES: This AD becomes effective April 13, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of April 13, 
2006.

ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
room PL-401, Washington, DC.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Nick Kusz, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6432; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (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 street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to certain Boeing Model 
747-200C, -200F, -400, -400D, and -400F series airplanes. That NPRM was 
published in the Federal Register on December 6, 2005 (70 FR 72599). 
That NPRM proposed to require repetitive inspections for cracks in the 
overlapping (upper) skin, upper fastener row of the lap joints of the 
fuselage skin in sections 41, 42, and 46; and related investigative and 
corrective actions, if necessary.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received. The 
commenter, Boeing, supports the NPRM.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD as proposed.

Costs of Compliance

    There are about 796 airplanes of the affected design in the 
worldwide fleet. This AD affects about 153 airplanes of U.S. registry. 
The required inspections will take about 534 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 $5,310,630, or 
$34,710 per airplane, per inspection cycle.

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 and placed it in the AD docket. 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2006-05-09 Boeing: Amendment 39-14506. Docket No. FAA-2005-23196; 
Directorate Identifier 2005-NM-187-AD.

Effective Date

    (a) This AD becomes effective April 13, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 747-200C, -200F, -400, -
400D, and -400F series airplanes, certificated in any category; as 
identified in Boeing Alert Service Bulletin 747-53A2499, dated 
August 11, 2005.

Unsafe Condition

    (d) This AD results from fatigue tests and an analysis that 
identified areas of the fuselage lap joints where fatigue cracks can 
occur. We are issuing this AD to detect and correct fatigue cracks 
in the overlapping (upper) skin, upper fastener row of the lap 
joints of the fuselage skin in sections 41, 42, and 46, which could 
adversely affect the structural integrity 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.

Initial Inspections and Related Investigative and Corrective Actions

    (f) At the applicable time specified in Table 1 of this AD: Do 
an external surface high frequency eddy current (HFEC), external low 
frequency eddy current (LFEC), and internal LFEC inspection, as 
applicable, for cracks in the overlapping (upper) skin, upper 
fastener row of the lap joints of the fuselage skin in sections 41, 
42, and 46, and any applicable related investigative and corrective 
actions by doing all of the actions in accordance with the 
Accomplishment Instructions of Boeing

[[Page 12124]]

Alert Service Bulletin 747-53A2499, dated August 11, 2005, except as 
provided by paragraph (h) of this AD. Do any applicable related 
investigative and corrective actions before further flight.

                    Table 1.--Initial Compliance Time
------------------------------------------------------------------------
   For airplanes on which Structural
 Significant Items (SSIs) F-25G, F-25H,             Inspect--
              and F-25I--
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(1) Have not been inspected in           Before the accumulation of
 accordance with paragraph (d) of AD      22,000 total flight cycles, or
 2004-07-22, amendment 39-13566 (69 FR    within 1,000 flight cycles
 24063, May 3, 2004), using the HFEC      after the effective date of
 method.                                  this AD, whichever occurs
                                          later.
(2) Have been inspected in accordance    Within 3,000 flight cycles
 with paragraph (d) of AD 2004-07-22,     after the most recent
 using the HFEC method.                   supplemental structural
                                          inspection document (SSID)
                                          inspection of each applicable
                                          structural significant item
                                          (as given in Boeing Document
                                          D6-35022, ``SSID for Model 747
                                          Airplanes,'' Revision G, dated
                                          December 2000), or within
                                          1,000 flight cycles after the
                                          effective date of this AD,
                                          whichever occurs later.
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Repetitive Inspections

    (g) Repeat the applicable inspections required by paragraph (f) 
of this AD thereafter at intervals not to exceed those specified in 
paragraph 1.E., ``Compliance'' (including the note) of Boeing Alert 
Service Bulletin 747-53A2499, dated August 11, 2005.

Exception to Service Bulletin Instructions

    (h) Where the service bulletin specifies to contact Boeing for 
appropriate action, before further flight, repair the crack using a 
method approved in accordance with the procedures specified in 
paragraph (i) of this AD.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.
    (3) 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 Commercial Airplanes 
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

    (j) You must use Boeing Alert Service Bulletin 747-53A2499, 
dated August 11, 2005, to perform the actions that are required by 
this AD, unless the AD specifies otherwise. The Director of the 
Federal Register approved the incorporation by reference of this 
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for a copy of this service information. You 
may review copies at the Docket Management Facility, U.S. Department 
of Transportation, 400 Seventh Street, SW., room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on February 27, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-2142 Filed 3-8-06; 8:45 am]
BILLING CODE 4910-13-P