[Federal Register Volume 65, Number 197 (Wednesday, October 11, 2000)]
[Rules and Regulations]
[Pages 60347-60349]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-25532]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-286-AD; Amendment 39-11927; AD 2000-20-16]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 757-200 Series Airplanes

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 757-200 series airplanes. This 
action requires repetitive inspections of the cargo loader system in 
the forward and aft cargo compartments to detect discrepancies, and 
corrective actions, if necessary. This action is necessary to detect 
and correct such discrepancies, which could result in reduced 
structural integrity of the fuselage and consequent cabin 
depressurization.

DATES: Effective October 26, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 26, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before December 11, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-286-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 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. 2000-NM-286-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 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 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.

FOR FURTHER INFORMATION CONTACT: Dennis Stremick, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2776; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: The FAA has received reports indicating 
that, on certain Boeing Model 757-200 series airplanes, damage has been 
detected to the fiberglass pan and fuselage frames located in the 
forward and aft cargo compartments. This damage has been attributed to 
incorrect operation of the cargo loader system and subsequent wear 
damage completely through the fiberglass pan, and in some cases, to the 
adjacent fuselage frames. This condition, if not corrected, could 
result in reduced structural integrity of the airplane fuselage and 
consequent cabin depressurization.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
757-25A0233, dated August 10, 2000, which describes procedures for 
repetitive inspections of the cargo loader system in the forward and 
aft cargo compartments to detect discrepancies (i.e., improper 
operation, wear damage of the fiberglass pan and fuselage frames), and 
corrective actions, if necessary.
    The corrective actions include procedures for repair of the cargo 
loader system if incorrectly installed or deactivation of the system if 
the fiberglass pan is worn to the extent that fibers are exposed; 
follow-on inspection of the fuselage frames if there is a hole worn 
through the fiberglass pan anywhere within the two-inches forward or 
aft of any frame location; repair or replacement of the damaged pan; 
and repair of the fuselage frames if damaged and damage is within the 
limits specified in the structural repair manual, as described in the 
alert service bulletin. Following accomplishment of the corrective 
actions, the alert service bulletin recommends testing the cargo loader 
system for proper operation. The alert service bulletin also contains 
instructions to contact the manufacturer for reactivation of the cargo 
loader system and disposition of certain inspection and repair 
procedures.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, this AD 
would require accomplishment of the actions specified in the alert 
service bulletin described previously, except as discussed below.

Differences Between Alert Service Bulletin and This AD

    Operators should note that, although the alert service bulletin 
permits reactivation of the cargo loader system after contacting the 
manufacturer for disposition of inspection and repair procedures, this 
AD requires reactivation of the system and disposition of the 
inspection and repair procedures be accomplished in accordance with a 
method approved by the FAA.
    Although the alert service bulletin specifies accomplishment of 
inspections, this AD refers to those inspections as detailed visual 
inspections. The FAA finds that ``detailed visual inspection'' is the 
appropriate terminology for the inspections described in the service 
bulletin. Additionally, a definition of a detailed visual inspection is 
included in Note 2 of this proposed AD.
    The alert service bulletin also specifies repetitive inspections at 
intervals not to exceed 300 flight cycles

[[Page 60348]]

provided no damage is detected following accomplishment of the initial 
inspection. However, paragraph (a) of this AD also requires 
accomplishment of the repetitive inspections if the cargo loader system 
is reactivated after damage is repaired.

Interim Action

    This is considered to be interim action. The manufacturer has 
advised that it currently is developing a modification that will 
positively address the unsafe condition addressed by this AD. Once this 
modification is developed, approved, and available, the FAA 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:
     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.
     For each issue, state what specific change to the AD is 
being requested.
     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 2000-NM-286-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:

2000-20-16  Boeing: Amendment 39-11927. Docket 2000-NM-286-AD.

    Applicability: Model 757-200 series airplanes, certificated in 
any category, having Air Cargo Equipment cargo loader systems.

    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 (c) 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 detect and correct discrepancies of the cargo loader system 
in the forward and aft cargo compartments, which could result in 
reduced structural integrity of the fuselage and consequent cabin 
depressurization, accomplish the following:

Repetitive Inspections

    (a) Within 60 days or 300 flight cycles after the effective date 
of this AD, whichever occurs first: Perform a detailed visual 
inspection of the cargo loader system in the forward and aft cargo 
compartments to detect discrepancies (i.e., improper operation, wear 
damage of the fiberglass pan and fuselage frames), in accordance 
with the Accomplishment Instructions of Boeing Alert Service 
Bulletin 757-25A0233, dated August 10, 2000. If no discrepancies are 
detected, or the cargo loader system is reactivated after repair of 
damage, repeat the inspection thereafter at intervals not to exceed 
300 flight cycles.

    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.''

Corrective Actions

    (b) If any discrepancies (i.e., improper operation, wear damage 
of the fiberglass pan or fuselage frames), are detected during any 
inspection required by paragraph (a) of this AD, before further 
flight: Repair the discrepancies and deactivate the cargo loader 
system in accordance with Boeing Alert Service Bulletin 757-25A0233, 
dated August 10, 2000. Further, if the damage to the

[[Page 60349]]

fuselage frame(s) is greater than the limits shown in the 757 
Structural Repair Manual, accomplish the repair in accordance with a 
method approved by the Manager, Seattle Aircraft Certification 
Office (ACO), FAA. Reactivate the cargo loader system only in 
accordance with a method 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.

Alternative Methods of Compliance

    (c) 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

    (d) 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

    (e) Except as provided by paragraph (b) of this AD, the actions 
shall be done in accordance with Boeing Alert Service Bulletin 757-
25A0233, dated August 10, 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

    (f) This amendment becomes effective on October 26, 2000.

    Issued in Renton, Washington, on September 29, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-25532 Filed 10-10-00; 8:45 am]
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