[Federal Register Volume 66, Number 144 (Thursday, July 26, 2001)]
[Rules and Regulations]
[Pages 38891-38892]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-18019]



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 Rules and Regulations
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  Federal Register / Vol. 66, No. 144 / Thursday, July 26, 2001 / Rules 
and Regulations  

[[Page 38891]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-346-AD; Amendment 39-12333; AD 2001-14-22]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100 and -200 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Boeing Model 747-100 and -200 series airplanes, 
that requires repetitive inspections for cracking of the station 800 
frame assembly, and repair, if necessary. The actions specified by this 
AD are intended to find and fix fatigue cracks that could extend and 
fully sever the frame, which could result in development of skin cracks 
that could lead to rapid depressurization of the airplane. This action 
is intended to address the identified unsafe condition.

DATES: Effective August 30, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 30, 2001.

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) 
227-1153; fax (425) 227-1181.

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 747-100 and -
200 series airplanes was published in the Federal Register on April 19, 
2001 (66 FR 20114). That action proposed to require repetitive 
inspections for cracking of the station 800 frame assembly, and repair, 
if necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 258 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 139 airplanes of U.S. registry 
will be affected by this AD, that it will take up to 14 work hours per 
airplane to accomplish the required inspection, and that the average 
labor rate is $60 per work hour. Based on these figures, the cost 
impact of the AD on U.S. operators is estimated to be as much as 
$116,760, or $840 per airplane, per inspection cycle.
    The cost impact figure discussed above is 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

    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

    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]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2001-14-22  Boeing: Amendment 39-12333. Docket 2000-NM-346-AD.

    Applicability: Model 747-100 and -200 series airplanes, as 
listed in Boeing Alert Service Bulletin 747-53A2451, including 
Appendix A, dated October 5, 2000, certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability

[[Page 38892]]

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 fatigue cracks of the station 800 frame assembly 
that could extend and fully sever the frame, which could result in 
development of skin cracks that could lead to rapid depressurization 
of the airplane, accomplish the following:

Repetitive Inspections

    (a) Do detailed visual, surface high frequency eddy current 
(HFEC), and open hole HFEC inspections, as applicable, for cracking 
of the station 800 frame assembly (including the inner chord strap, 
angles, and exposed web) between stringers 14 and 18, according to 
Boeing Alert Service Bulletin 747-53A2451, including Appendix A, 
dated October 5, 2000. Except as provided by paragraph (b) of this 
AD, do the inspection at the applicable time specified in Table 1 
below, and repeat the inspections thereafter at least every 3,000 
flight cycles: Table 1 is as follows:

                       Table 1.--Compliance Times
------------------------------------------------------------------------
Total flight cycles as of the effective   Do the inspection in paragraph
            date of this AD                      (a) at this time
------------------------------------------------------------------------
(1) Fewer than 19,000..................  Before the accumulation of
                                          19,000 total flight cycles, or
                                          within 1,500 flight cycles
                                          after the effective date of
                                          this AD, whichever comes
                                          later.
(2) 19,000 or more but 24,250 or fewer.  Within 1,500 flight cycles or
                                          12 months after the effective
                                          date of this AD, whichever
                                          comes first.
(3) 24,251 or more.....................  Within 750 flight cycles or 12
                                          months after the effective
                                          date of this AD, whichever
                                          comes first.
------------------------------------------------------------------------


    Note 2: For the purposes of this AD, a detailed visual 
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.''

Adjustments to Compliance Time: Cabin Differential Pressure

    (b) For the purposes of calculating the compliance threshold and 
repetitive interval for the actions required by paragraph (a) of 
this AD, the number of flight cycles in which cabin differential 
pressure is at 2.0 pounds per square inch (psi) or less need not be 
counted when determining the number of flight cycles that have 
occurred on the airplane, provided that flight cycles with momentary 
spikes in cabin differential pressure above 2.0 psi are included as 
full pressure cycles. For this provision to apply, all cabin 
pressure records must be maintained for each airplane: NO fleet-
averaging of cabin pressure is allowed.

Repair

    (c) If any cracking is detected during any inspection required 
by paragraph (a) of this AD, before further flight, repair the 
cracking according to a method approved by the Manager, Seattle 
Aircraft Certification Office (ACO), FAA; or according to 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 by the Manager, Seattle ACO, as 
required by this paragraph, the approval letter must specifically 
reference 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) Except as provided by paragraphs (b) and (c) of this AD, the 
actions shall be done in accordance with Boeing Alert Service 
Bulletin 747-53A2451, including Appendix A, dated October 5, 2000. 
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 August 30, 2001.

    Issued in Renton, Washington, on July 12, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-18019 Filed 7-25-01; 8:45 am]
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