[Federal Register Volume 69, Number 59 (Friday, March 26, 2004)]
[Rules and Regulations]
[Pages 15663-15664]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-6579]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-288-AD; Amendment 39-13538; AD 2004-06-12]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-400F 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 747-400F series airplanes, that 
requires repetitive detailed and general visual inspections of the 
external fuselage skin for cracks; various inspections of the affected 
area where cracks are found to determine the extent of the damage; and 
repair of cracks. This action is necessary to detect and correct 
fatigue cracks in the fuselage skin and frame shear tie assemblies, 
which could propagate and result in possible in-flight decompression of 
the airplane. This action is intended to address the identified unsafe 
condition.

DATES: Effective April 30, 2004.
    The incorporation by reference of a certain publication listed in 
the regulations is approved by the Director of the Federal Register as 
of April 30, 2004.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplanes, 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: Candice Gerretsen, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6428; fax (425) 917-6590.

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 747-400F 
series airplanes was published in the Federal Register on November 26, 
2003 (68 FR 66384). That action proposed to require repetitive detailed 
and general visual inspections of the external fuselage skin for 
cracks; various inspections of the affected area where cracks are found 
to determine the extent of the damage; and repair of cracks.

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 72 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 12 airplanes of U.S. registry 
will be affected by this AD, that it will take approximately 1 work 
hour per airplane to accomplish the required inspections, and that the 
average labor rate is $65 per work hour. Based on these figures, the 
cost impact of the AD on U.S. operators is estimated to be $780, or $65 
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. Manufacturer warranty remedies may be available 
for labor costs associated with this AD. As a result, the costs 
attributable to the AD may be less than stated above.

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.

[[Page 15664]]

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:

2004-06-12 Boeing: Amendment 39-13538. Docket 2002-NM-288-AD.

    Applicability: Model 747-400F series airplanes, having line 
numbers 968 through 1286 inclusive, certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct fatigue cracks in the fuselage skin and 
frame shear tie assemblies, which could propagate and result in 
possible in-flight decompression of the airplane, accomplish the 
following:

Service Bulletin Reference

    (a) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2480, dated March 28, 2002.

Compliance Time

    (b) At the later compliance time specified in paragraphs (b)(1) 
and (b)(2) of this AD, do the inspections specified in paragraph (c) 
of this AD.
    (1) Within 6,000 flight cycles after the date of issuance of the 
original Airworthiness Certificate or date of issuance of the Export 
Certificate of Airworthiness, whichever comes first.
    (2) Within 3,000 flight cycles after the effective date of this 
AD.

Repetitive Inspections

    (c) Perform both inspections of the external fuselage skin as 
shown in Table 1 of this AD, per the service bulletin. Repeat the 
inspections thereafter at intervals not to exceed 3,000 flight 
cycles.

                    Table 1.--Inspection Requirements
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        Type of inspection                     Area to inspect
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(1) Detailed......................  Inspect the skin surface for cracks
                                     initiating from the shear tie
                                     fasteners (14 locations on each
                                     side) common to the body station
                                     800 frame between stringers S-13
                                     and S-15 on both the left and right
                                     sides of the airplane.
(2) General visual................  Inspect the skin surface at all
                                     fastener locations for cracks
                                     between body stations 780 to 800
                                     and stringers S-13 through S-15 on
                                     both the left and right sides of
                                     the airplane.
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    Note 1: 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.''


    Note 2: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made from within 
touching distance unless otherwise specified. A mirror may be 
necessary to enhance visual access to all exposed surfaces in the 
inspection area. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or droplight and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

Crack Findings: Inspections and Repair

    (d) If any crack is found during any inspection required by 
paragraph (c) of this AD, before further flight, do the actions 
specified in paragraphs (d)(1) and (d)(2) of this AD.
    (1) Perform inspections of the affected area to determine the 
extent of the crack using the following applicable inspection 
methods, per the service bulletin: detailed inspection; open-hole 
high frequency eddy current (HFEC) inspection; surface HFEC 
inspection; and dye penetrant inspection.
    (2) Repair any crack per the service bulletin. Where the service 
bulletin specifies contacting Boeing for an alternate repair method: 
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 DER who has been authorized by the Manager, Seattle 
ACO, to make such findings.

Terminating Action for Repaired Area

    (e) Accomplishment of the repair per paragraph (d)(2) of this AD 
ends the repetitive inspection requirements of paragraph (c) of this 
AD for that repaired area only.

Alternative Methods of Compliance

    (f) In accordance with 14 CFR 39.19, the Manager, Seattle ACO, 
FAA, is authorized to approve alternative methods of compliance 
(AMOCs) for this AD.

Incorporation by Reference

    (g) Unless otherwise specified in this AD, the actions shall be 
done in accordance with Boeing Special Attention Service Bulletin 
747-53-2480, dated March 28, 2002. 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 Airplanes, 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

    (h) This amendment becomes effective on April 30, 2004.

    Issued in Renton, Washington, on March 16, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-6579 Filed 3-25-04; 8:45 am]
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