[Federal Register Volume 70, Number 142 (Tuesday, July 26, 2005)]
[Rules and Regulations]
[Pages 43020-43022]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-14396]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19175; Directorate Identifier 2003-NM-246-AD; 
Amendment 39-14197; AD 2005-15-08]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100B SUD, -200B, -300, 
-400, and -400D 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 747-100B SUD, -200B, -300, -400, and -400D series 
airplanes. This AD requires repetitive inspections for cracking in 
fuselage stringers 8L, 8R, 10L, and 10R at body stations 460, 480, and 
500 frame locations; and repair if necessary. This AD is prompted by 
findings of cracking in fuselage stringers 8L, 8R, 10L, and 10R at body 
stations 460, 480, and 500 frame locations. We are issuing this AD to 
detect and correct fatigue cracking in certain fuselage stringers, 
which, if left undetected, could result in fuselage skin cracking that 
reduces the structural integrity of the skin panel, and consequent 
rapid depressurization of the airplane.

DATES: This AD becomes effective August 30, 2005.
    The incorporation by reference of a certain publication listed in 
the AD is approved by the Director of the Federal Register as of August 
30, 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 
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 U.S. 
Department of Transportation, 400 Seventh Street SW., room PL-401, 
Washington, DC. This docket number is FAA-2004-19175; the directorate 
identifier for this docket is 2003-NM-246-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: The FAA proposed to amend 14 CFR part 39 
with an AD for certain Boeing Model 747-100B SUD, -200B, -300, -400, 
and -400D series airplanes. That action, published in the Federal 
Register on September 28, 2004 (69 FR 57884), proposed to require 
repetitive inspections for cracking in fuselage stringers 8L, 8R, 10L, 
and 10R at body stations 460, 480, and 500 frame locations; and repair 
if necessary.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
submitted on the proposed AD.

Support for the Proposed AD

    One commenter concurs with the FAA's compliance recommendations 
specified in the proposed AD. A second commenter, the manufacturer, 
requested that the compliance time be changed to match the referenced 
service bulletin; the commenter later submitted a comment stating that 
it reanalyzed the data and now concurs with the compliance time 
specified in the proposed AD.

Request for Clarification of the Compliance Time

    One commenter states that paragraph (f) of the proposed AD 
specifies repeating the inspection at intervals not to exceed 3,000 
flight cycles until the optional terminating action is accomplished. 
The commenter adds that the referenced service bulletin recommends 
inspections at specific thresholds that equate to a 3,000-flight-cycle 
interval, until the airplane accumulates 25,000 flight cycles. The 
commenter also notes that the referenced service bulletin recommends 
that airplanes having more than 25,000 total flight cycles be inspected 
at intervals not to exceed 2,000 flight cycles, and adds that the 
proposed AD does not seem to address this situation. The commenter asks 
that the preamble in the proposed AD clearly specify that the 3,000-
flight-cycle interval cited in paragraph (f) replaces the threshold 
values in the referenced service bulletin.
    Although we acknowledge the commenter's concern, the difference in 
compliance times was explained in the proposed AD. In the section 
titled ``Differences Between the Proposed AD and Service Information'' 
of the preamble of the proposed AD, we define the difference in 
compliance times, as follows: ``The manufacturer reanalyzed the service 
problem and has advised the FAA that the reanalysis has resulted in 
threshold and repetitive inspection intervals different from the 
service bulletin. This resulted in simplified initial thresholds and an 
increased number of flight cycles between repetitive inspections.'' 
That section of the preamble of the proposed AD is not restated in the 
final rule; therefore, we made no change to the final rule in this 
regard.

Request for Optional Open-Hole and Surface High Frequency Eddy Current 
(HFEC) Inspections To Extend Repetitive Inspection Intervals

    One commenter states that, subsequent to the release of the 
referenced service bulletin, Boeing advised the commenter of optional 
open-hole and surface HFEC inspections that could be performed in 
addition to the specified detailed inspections. The commenter adds that 
these optional inspections would allow extending the repetitive 
inspection interval to 4,000 flight cycles, until the accumulation of 
25,000 total flight cycles on the airplane. The commenter asks that the 
FAA consult with Boeing about this alternative inspection process and, 
if appropriate, include that option in the final rule.
    Although we acknowledge that the optional inspections may be a 
viable alternative to the detailed inspections, we have confirmed with 
the manufacturer that while an open-hole and surface HFEC inspection 
may be accomplished, there are no existing procedures available. 
Therefore, we do not agree to add the optional inspections and extend 
the repetitive inspection interval in this final rule. Paragraph (i) of 
this AD provides affected operators the opportunity to apply for an 
alternative method of compliance (AMOC) and to present data to justify 
adding the optional inspections and extending the repetitive inspection 
interval. In addition, if the referenced service information is revised 
to add the optional inspections, we may approve it as an AMOC to the 
final rule, if appropriate. We have made no change to the final rule in 
this regard.

[[Page 43021]]

Request To Change Costs of Compliance Section

    One commenter states that the proposed AD cites 3 work hours for 
accomplishing the inspection, and uses this estimate to determine the 
cost of compliance. The commenter notes that although 3 hours to 
accomplish the inspection is valid, no consideration is given for 
access and restoration, which can require up to 61 work hours for each 
airplane per the referenced service information. The commenter adds 
that it is inappropriate and unrealistic to cite a cost of compliance 
that fails to account for access and restoration when such tasks do not 
occur frequently enough to warrant them as negligible. The commenter 
asks that the cost of compliance be recalculated to include the work 
hours for access and restoration.
    We do not agree to change the work hours in this AD. This number 
represents the time necessary to perform only the action actually 
required by the AD. The action in this final rule reflects only the 
direct costs of the specific required action (inspection) based on the 
best data available from the manufacturer. The cost analysis in AD 
rulemaking actions typically does not include incidental costs such as 
the time required to gain access and close up, time necessary for 
planning, or time necessitated by other administrative actions. Those 
incidental costs, which may vary significantly among operators, are 
almost impossible to calculate. We have made no change to the final 
rule in this regard.

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.

Costs of Compliance

    This AD will affect about 243 Boeing Model 747-100B SUD, -200B, -
300, -400, and -400D series airplanes worldwide. The following table 
provides the estimated costs for U.S. operators to comply with this AD.

                                                 Estimated Costs
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                                                                                         Number of
                                                  Average                    Cost per      U.S.-
              Action                Work hours   labor rate      Parts       airplane    registered   Fleet cost
                                                  per hour                               airplanes
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Inspection.......................            3          $65  None........         $195           69      $13,455
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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):

2005-15-08 Boeing: Amendment 39-14197. Docket No. FAA-2004-19175; 
Directorate Identifier 2003-NM-246-AD.

Effective Date

    (a) This AD becomes effective August 30, 2005.

Affected ADs

    (b) None.
    Applicability: (c) This AD applies to certain Boeing Model 747-
100B SUD, -200B, -300, -400, and -400D series airplanes; 
certificated in any category; as listed in Boeing Alert Service 
Bulletin 747-53A2484, dated June 26, 2003.

Unsafe Condition

    (d) This AD was prompted by findings of cracking in fuselage 
stringers 8L, 8R, 10L, and 10R at body station 460, 480, and 500 
frame locations. We are issuing this AD to detect and correct 
fatigue cracking in the specified fuselage stringers, which, if left 
undetected, could result in fuselage skin cracking that reduces the 
structural integrity of the skin panel, 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.

Inspection

    (f) Do a detailed inspection for cracking in fuselage stringers 
8L, 8R, 10L, and 10R at body station 460, 480, and 500 frame 
locations, in accordance with Part 1 of the Accomplishment 
Instructions in Boeing Alert Service Bulletin 747-53A2484, dated 
June 26, 2003. Do the inspections at the applicable time specified 
in paragraph (f)(1) or (f)(2) of this AD. Repeat the inspection 
thereafter at intervals not to exceed 3,000 flight cycles until the 
requirements of paragraph (h) of this AD are accomplished.

[[Page 43022]]

    (1) For airplanes with 19,000 total flight cycles or less as of 
the effective date of this AD: Prior to the accumulation of 8,000 
total flight cycles or within 2,000 flight cycles after the 
effective date of this AD, whichever is later, not to exceed 20,000 
total flight cycles.
    (2) For airplanes with more than 19,000 total flight cycles as 
of the effective date of this AD: Within 1,000 flight cycles after 
the effective date of this AD.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

Repair

    (g) If any cracking is found during any inspection required by 
paragraph (f) of this AD: Before further flight, repair the affected 
stringer in accordance with Part 2 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2484, dated 
June 26, 2003. Repair terminates the repetitive inspections required 
by paragraph (f) of this AD for only the repaired stringer/frame 
location.

Optional Terminating Action

    (h) Installing new frame clips and new doublers, and repairing 
as applicable, in accordance with Part 3 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2484, dated 
June 26, 2003, terminates the repetitive inspections required by 
this AD.

Alternative Methods of Compliance (AMOCs)

    (i) The Manager, Seattle Aircraft Certification Office, FAA, has 
the authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19.

Material Incorporated by Reference

    (j) You must use Boeing Alert Service Bulletin 747-53A2484, 
dated June 26, 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. To 
get copies of the service information, contact Boeing Commercial 
Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. To view 
the AD docket, go to the Docket Management Facility, U.S. Department 
of Transportation, 400 Seventh Street SW., room PL-401, Nassif 
Building, Washington, DC. To review copies of the service 
information, go to 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 July 13, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-14396 Filed 7-25-05; 8:45 am]
BILLING CODE 4910-13-P