[Federal Register Volume 67, Number 228 (Tuesday, November 26, 2002)]
[Rules and Regulations]
[Pages 70680-70682]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-29675]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-270-AD; Amendment 39-12959; AD 2002-23-15]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100, -200B, -200C, -
200F, -300, -400, -400F, and 747SR Series Airplanes, Equipped with a 
Main Deck Side Cargo Door (MDSCD) Manufactured by Boeing

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Boeing Model 747-100, -200B, -200C, -200F, -
300, -400, -400F, and 747SR series airplanes equipped with a MCSCD 
manufactured by Boeing. This action requires repetitive inspections for 
cracking of the lower lobe panel of the fuselage skin of the aft cargo 
bay, and repair if necessary. This action is necessary to find and fix 
cracking of the skin, which could lead to reduced structural integrity 
of the side cargo door cutout of the main deck, and result in rapid 
depressurization of the airplane. This action is intended to address 
the identified unsafe condition.

DATES: Effective December 11, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 11, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before January 27, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-270-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2002-NM-270-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2131; 
fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: The FAA recently received a report of 
cracking of the lower lobe panel of the fuselage skin of the aft cargo 
bay, between Station (STA) 1720 and 1740, on a Model 747-200F series 
airplane. The crack was 11.6 inches long and was located below the 
stringer 34L lap joint and the upper fastener row of the external 
reinforcing doubler of the cargo door cutout of the main deck. The 
airplane had accumulated 18,688 total flight cycles and 81,902 total 
flight hours. Subsequent examination and analysis of the cracked skin 
revealed that the crack originated from scratches in the skin exterior 
surface at multiple locations. Such cracking, if not found and fixed, 
could lead to reduced structural integrity of the side cargo door 
cutout of the main deck, and result in rapid depressurization of the 
airplane.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
747-53A2487, Revision 1, dated October 31, 2002, which describes 
procedures for repetitive internal detailed or eddy current inspections 
for cracking of the lower lobe panel of the fuselage skin of the aft 
cargo bay at section 46, below stringer 34L, from STA 1640 through 1740 
inclusive. If any cracking is found, the service bulletin specifies 
contacting the manufacturer for repair information. The service 
bulletin also recommends that operators submit inspection findings to 
Boeing following each inspection. Accomplishment of the actions 
specified in the service bulletin is intended to adequately address the 
identified unsafe condition.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design, this AD 
requires

[[Page 70681]]

accomplishment of the actions specified in the service bulletin 
described previously, except as discussed below.

Differences Between AD and Service Bulletin

    The service bulletin specifies that the manufacturer may be 
contacted for disposition of repairs; however, this AD requires all 
repairs to be accomplished per a method approved by the 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 Aircraft Certification Office, to 
make such findings.
    Although the service bulletin recommends that operators report 
findings to the manufacturer after each inspection, this AD does not 
include such a reporting requirement.

Interim Action

    This is considered to be interim action. The manufacturer has 
advised that it currently is developing a modification that will 
address the unsafe condition addressed by this AD. Once this 
modification is developed, approved, and available, we may consider 
additional rulemaking.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications shall identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Submit comments using the following format:
    [sbull] Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    [sbull] For each issue, state what specific change to the AD is 
being requested.
    [sbull] Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2002-NM-270-AD.'' The postcard will be date stamped 
and returned to the commenter.

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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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:

2002-23-15 Boeing: Amendment 39-12959. Docket 2002-NM-270-AD.

    Applicability: Model 747-100, -200B, -200C, -200F, -300, -400, -
400F, and 747SR series airplanes; equipped with a main deck side 
cargo door manufactured by Boeing; 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 cracking of the lower lobe panel of the fuselage 
skin of the aft cargo bay, which could lead to reduced structural 
integrity of the side cargo door cutout of the main deck, and result 
in rapid depressurization of the airplane, accomplish the following:

Repetitive Inspections

    (a) Do either an internal detailed or eddy current inspection to 
find cracking of the lower lobe panel of the fuselage skin of the 
aft cargo bay, below stringer 34L, from Station (STA) 1640 through 
1740 inclusive, per Boeing Alert Service Bulletin 747-53A2487, 
Revision 1, dated October 31, 2002. Do the initial inspection at the 
time shown in paragraph (a)(1) or (a)(2) of this AD, as applicable. 
If the initial inspection was a detailed inspection, repeat that 
inspection at least every 50 flight cycles; if the initial 
inspection was an eddy current inspection, repeat that inspection at 
least every 250 flight cycles; as applicable. Although the service 
bulletin references a reporting requirement in paragraph 1.D., such 
reporting is not required by this AD.


[[Page 70682]]


    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.''

    (1) For airplanes on which the main deck side cargo door (MDSCD) 
was installed after the date of manufacture of the airplane: Do the 
inspection within 10,000 flight cycles after installation of the 
MDSCD, or within 90 days after the effective date of this AD, 
whichever is later.
    (2) For airplanes on which the MDSCD was installed before the 
date of manufacture of the airplane: Do the inspection prior to the 
accumulation of 15,000 total flight cycles on the airplane, or 
within 90 days after the effective date of this AD, whichever is 
later.
    (b) Inspections done before the effective date of this AD per 
Boeing Alert Service Bulletin 747-53A2487, dated October 24, 2000; 
are considered acceptable for compliance with paragraph (a) of this 
AD.

Repair

    (c) If any crack is found during any inspection required by 
paragraph (a) of this AD: 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 by the 
Manager, Seattle ACO, as required by this paragraph, the Manager's 
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) Unless otherwise provided by this AD, the actions shall be 
done in accordance with Boeing Alert Service Bulletin 747-53A2487, 
Revision 1, dated October 31, 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 Airplane Group, PO 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 December 11, 2002.

    Issued in Renton, Washington, on November 14, 2002.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-29675 Filed 11-25-02; 8:45 am]
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