[Federal Register: May 7, 2004 (Volume 69, Number 89)]
[Rules and Regulations]
[Page 25481-25483]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07my04-2]
[[Page 25481]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2004-NM-44-AD; Amendment 39-13622; AD 2004-09-32]
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 initial and repetitive inspections of the fuselage skin
and bear strap at the forward, upper corner of the L1 entry door cutout
for cracking, and repair if necessary. This action also provides an
optional terminating action for the repetitive inspections. This action
is necessary to detect and correct cracking of the fuselage skin and
bear strap at the forward, upper corner of the L1 entry door cutout,
which could result in reduced structural integrity of the L1 entry door
and consequent rapid decompression of the airplane. This action is
intended to address the identified unsafe condition.
DATES: Effective May 24, 2004.
The incorporation by reference of a certain publication listed in
the regulations is approved by the Director of the Federal Register as
of May 24, 2004.
Comments for inclusion in the Rules Docket must be received on or
before July 6, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2004-NM-44-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:
9-anm-iarcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2004-NM-44-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 or 2000 or
ASCII text.
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 FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
National Archives and Records Administration (NARA). For information on
the availability of this material at NARA, call (202) 741-6030, or go
to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
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)
917-6450; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: The FAA has received reports of cracking in
the fuselage skin and bear strap at the forward, upper corner of the L1
entry door cutout on Boeing Model 757-200 series airplanes. A 6.0-inch
crack was found on an airplane having 27,071 total flight cycles. A
1.4-inch crack was also found on an airplane having 29,340 total flight
cycles, and a 1.7-inch crack was found in the bear strap on an airplane
having 26,686 total flight cycles. These cracks were found during
visual inspections during maintenance and were attributed to fatigue
caused by pressurization cycles.
This condition, if not corrected, could result in reduced
structural integrity of the L1 entry door and consequent rapid
decompression of the airplane.
Explanation of Relevant Service Information
The FAA has reviewed and approved Boeing Special Attention Service
Bulletin 757-53-0089, dated March 18, 2004. The service bulletin
describes procedures for performing initial and repetitive high
frequency eddy current (HFEC) and low frequency eddy current (LFEC)
inspections for cracking of the fuselage skin around the adjacent
fasteners, along the edge of the skin and bear strap, and the bear
strap around the fasteners adjacent at the forward, upper corner of the
L1 entry door cutout; as applicable. The service bulletin specifies to
contact Boeing for repair instructions for any cracks found during the
HFEC and LFEC inspections.
The service bulletin also describes procedures for accomplishing a
preventative modification, which eliminates the need for the repetitive
inspections. The modification includes performing a general visual
inspection to ensure that the fastener edge margins adjacent to the
forward, upper corner of the L1 entry door cutout are 0.5 inch or
greater; and related investigative/corrective actions, if necessary.
Related investigative actions include repeating the general visual
inspection at specified intervals if the margins are less than 0.50
inch or removing the fasteners and performing an HFEC inspection on the
holes in the fuselage skin and bear strap if the margins are equal to
or greater than 0.50 inch. The corrective actions include coldworking
the fastener holes and installing over-sized fasteners if no crack is
found during the HFEC inspection or contacting Boeing for repair
instructions if any crack is found during either the general visual or
the HFEC 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 registered
in the United States, this AD requires accomplishment of the actions
specified in the service bulletin described previously, except as
discussed below. This AD also provides for optional terminating action
for the repetitive inspections.
Differences Between This AD and the Service Bulletin
Although the service bulletin specifies that operators contact the
manufacturer for disposition of certain repair conditions, this AD
requires operators to repair those conditions 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 FAA to make such
findings.
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
[[Page 25482]]
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 2004-NM-44-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
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:
2004-09-32 Boeing: Amendment 39-13622. Docket 2004-NM-44-AD.
Applicability: Model 757-200 series airplanes, line numbers 1
through 90 inclusive; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct cracking of the fuselage skin and bear
strap at the forward, upper corner of the L1 entry door cutout,
which could result in reduced structural integrity of the L1 entry
door and consequent rapid decompression of the airplane; accomplish
the following:
Initial Inspections
(a) Within 500 flight cycles after the effective date of this
AD, or within 90 days after the effective date of this AD, whichever
occurs later: Do the inspections of the forward, upper corner of the
L1 entry door cutout specified in paragraphs (a)(1), (a)(2), and
(a)(3) of this AD, per Part 1 of the Work Instructions of Boeing
Special Attention Service Bulletin 757-53-0089, dated March 18,
2004.
(1) Do a high frequency eddy current (HFEC) inspection for
cracking of the fuselage skin around the adjacent fasteners.
(2) Do an HFEC inspection for cracking along the edge of the
skin and bear strap.
(3) Do a low frequency eddy current (LFEC) inspection of the
bear strap.
No Crack Detected: Repetitive Inspections
(b) If no crack is detected during any inspection required by
paragraph (a) of this AD: Repeat the inspections required by
paragraph (a) of this AD at intervals not to exceed 1,400 flight
cycles.
Any Crack Detected: Repair
(c) If any crack is detected during any inspection required by
this AD, and the service bulletin specifies to contact Boeing for
appropriate action: 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 (DER) 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.
Optional Terminating Modification
(d) As an alternative to accomplishing the inspections required
by paragraphs (a) and (b) of this AD, do the optional preventative
modification of the forward, upper corner of the L1 entry door
cutout, and do all applicable related investigative/corrective
actions by accomplishing all the actions specified in Part 2 of the
Work Instructions of Boeing Special Attention Service Bulletin 757-
53-0089, dated March 18, 2004. Accomplishment of the modification
constitutes terminating action for the repetitive inspection
requirements of this AD.
Alternative Methods of Compliance
(e)(1) In accordance with 14 CFR 39.19, the Manager, Seattle
ACO, FAA, is authorized to approve alternative methods of compliance
(AMOCs) for this AD.
(2) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by a
Boeing Company DER who has been authorized by the Manager, Seattle
ACO, to make such findings.
Incorporation by Reference
(f) Unless otherwise specified in this AD, the actions shall be
done in accordance with Boeing Special Attention Service Bulletin
757-53-0089, dated March 18, 2004. 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
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call (202) 741-6030,
or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Effective Date
(g) This amendment becomes effective on May 24, 2004.
[[Page 25483]]
Issued in Renton, Washington, on April 28, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-10240 Filed 5-6-04; 8:45 am]
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