[Federal Register Volume 68, Number 101 (Tuesday, May 27, 2003)]
[Rules and Regulations]
[Pages 28695-28697]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-12841]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-231-AD; Amendment 39-13154; AD 2003-10-09]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-400 and -400F Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Boeing Model 747-400 and -400F series airplanes, 
that requires initial and, for certain airplanes, repetitive 
inspections of the rivets in the forward, top, and side panels of the 
nose wheel well (NWW) for discrepancies; and follow-on inspections and 
corrective action, if necessary. This amendment also provides eventual 
terminating action for the repetitive inspections. The actions 
specified by this AD are intended to find and fix discrepancies of the 
rivets in the NWW panels, which could result in failure of the rivets 
and consequent reduced structural integrity of the panels and rapid 
depressurization of the airplane. This action is intended to address 
the identified unsafe condition.

DATES: Effective July 1, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 1, 2003.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Rick Kawaguchi, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6434; fax (425) 917-6535.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Boeing Model 747-400 and -
400F series

[[Page 28696]]

airplanes was published in the Federal Register on January 8, 2003 (68 
FR 1017). That action proposed to require initial and, for certain 
airplanes, repetitive inspections of the rivets in the forward, top, 
and side panels of the nose wheel well (NWW) for discrepancies; and 
follow-on inspections and corrective action, if necessary. That action 
also proposed to provide eventual terminating action for the repetitive 
inspections.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received. One commenter states that it does not own or 
operate the equipment affected by the proposed AD, and has no comments.

Request To Give Credit for Terminating Action

    One commenter asks that the compliance time specified in paragraph 
(c) of the proposed AD be changed from ``Within 2 years after the 
effective date of this AD'' to ``No later than 2 years after the date 
of this AD.'' The commenter states that this wording would give credit 
to operators that have previously performed the identical terminating 
action at a time prior to the eventual release of the final rule.
    The FAA agrees that any operator that has previously performed the 
terminating action required by paragraph (c) of the final rule does not 
have to do that action again. We already give credit for actions 
accomplished before the effective date of an AD by means of the phrase 
``Compliance: Required as indicated, unless accomplished previously,'' 
which appears in every AD. Therefore, no change to the final rule is 
necessary in this regard.

Explanation of Editorial Changes

    We have changed the service bulletin citation throughout this final 
rule to exclude the Evaluation Form. The form is intended to be 
completed by operators and submitted to the manufacturer to provide 
input on the quality of the service bulletin; however, this AD does not 
include such a requirement.
    We also have added a reference to the service bulletin in 
paragraphs (a)(1) and (c)(1) of this final rule for clarification.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 43 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 6 airplanes of U.S. registry 
will be affected by this AD.
    It will take approximately 4 work hours per airplane to do the 
detailed inspection, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the detailed inspection 
required by this AD on U.S. operators is estimated to be $1,440, or 
$240 per airplane, per inspection cycle.
    It will take approximately 10 work hours per airplane to do the 
indirect conductivity eddy current inspection, at an average labor rate 
of $60 per work hour. Based on these figures, the cost impact of the 
indirect conductivity eddy current inspection required by this AD on 
U.S. operators is estimated to be $3,600, or $600 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new airworthiness 
directive:

2003-10-09 Boeing: Amendment 39-13154. Docket 2001-NM-231-AD.

    Applicability: Model 747-400 and -400F series airplanes, line 
numbers 1141 through 1183 inclusive; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (d) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To find and fix discrepancies of the rivets in the nose wheel 
well (NWW) panels, which could result in failure of the rivets and 
consequent reduced structural integrity of the panels and rapid 
depressurization of the airplane, do the following:

Repetitive/Follow-on Inspections/Corrective Action

    (a) Within 6 months after the effective date of this AD: Do a 
detailed inspection of the forward, top, and side panels of the NWW 
for missing rivet heads, between fuselage stations 260 and 340 of 
the canted pressure bulkhead, per Figure 2 of the Work Instructions 
of Boeing Alert Service Bulletin 747-53A2472, including Appendix A, 
excluding Evaluation Form, dated June 7, 2001.

[[Page 28697]]

    (1) If any missing rivet head is found, before further flight, 
replace with a permanent or time limited repair fastener per the 
Work Instructions of the service bulletin, and do the actions 
specified in paragraph (b) of this AD.
    (2) If no missing rivet head is found, before further flight, do 
the actions required by paragraph (c) of this AD, or repeat the 
detailed inspection at least every 6 months until paragraph (c) of 
this AD is done.

    Note 2: For the purposes of this AD, a detailed inspection is 
defined as: ``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.''

    (b) If any missing rivet head is found during any inspection 
required by paragraph (a) of this AD: Within 30 days after doing the 
detailed inspection, do an indirect conductivity eddy current 
inspection for discrepant rivets (incorrectly heat-treated) per 
Figure 2 of the Work Instructions of Boeing Alert Service Bulletin 
747-53A2472, including Appendix A, excluding Evaluation Form, dated 
June 7, 2001. If any discrepant rivet is found, before further 
flight, replace with a permanent or time limited repair fastener as 
required by paragraph (b)(1) or (b)(2) of this AD, as applicable. If 
no discrepant rivet is found, no further action is required by this 
AD. Replace any time limited repair fasteners with permanent 
fasteners within 24 months after installation.
    (1) If up to three adjacent discrepant rivets are found: Before 
further flight, remove the affected rivets and replace with 
permanent or time limited repair fasteners per the Work Instructions 
of the service bulletin.
    (2) If four or more adjacent discrepant rivets are found: Before 
further flight, remove the affected rivets and do a high frequency 
eddy current inspection of the web for cracking around the intact 
fasteners at each end of the line of missing rivets per the Work 
Instructions of the service bulletin.
    (i) If no web cracking is found, before further flight, install 
permanent or time limited repair fasteners per the Work Instructions 
of the service bulletin.
    (ii) If any web cracking is found, before further flight, repair 
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 reference this AD.

Terminating Action

    (c) For airplanes on which no missing rivet head is found during 
the inspection required by paragraph (a) of this AD: Within 2 years 
after the effective date of this AD, do an indirect conductivity 
eddy current inspection for discrepant rivets (incorrectly heat-
treated) of the NWW panels between fuselage stations 260 and 340 of 
the canted pressure bulkhead per the Work Instructions of Boeing 
Alert Service Bulletin 747-53A2472, including Appendix A, excluding 
Evaluation Form, dated June 7, 2001.
    (1) If any discrepant rivet is found, before further flight, 
replace with a permanent or time limited repair fastener per the 
Work Instructions of the service bulletin. Replace any time limited 
repair fasteners with permanent fasteners within 24 months after 
installation.
    (2) If no discrepant rivet is found, no further action is 
required by this AD.

Alternative Methods of Compliance

    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Seattle ACO. Operators shall submit 
their requests through an appropriate FAA Principal Maintenance 
Inspector, who may add comments and then send it to the Manager, 
Seattle ACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (e) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (f) Unless otherwise provided in this AD, the actions shall be 
done in accordance with Boeing Alert Service Bulletin 747-53A2472, 
including Appendix A, excluding Evaluation Form, dated June 7, 2001. 
This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Boeing Commercial Airplane Group, 
P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., Suite 700, Washington, DC.

Effective Date

    (g) This amendment becomes effective on July 1, 2003.

    Issued in Renton, Washington, on May 16, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-12841 Filed 5-23-03; 8:45 am]
BILLING CODE 4910-13-P