[Federal Register: December 3, 2002 (Volume 67, Number 232)]
[Rules and Regulations]
[Page 71810-71812]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr03de02-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-192-AD; Amendment 39-12967; AD 2002-24-02]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 757-200 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 757-200 series airplanes, that
requires repetitive inspections for fatigue cracking of certain areas
of the forward and aft frames of the cargo doorways and repair, if
necessary. The actions specified by this AD are intended to find and
fix such cracking, which could lead to rapid depressurization of the
airplane and result in reduced structural integrity of the cargo
doorway. This action is intended to address the identified unsafe
condition.
DATES: Effective January 7, 2003.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 7, 2003.
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: 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: 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 757-200
series airplanes was published in the Federal Register on July 12, 2002
(67 FR 46132). That action proposed to require repetitive inspections
for fatigue cracking of certain areas of the forward and aft frames of
the cargo doorways, and repair, if necessary.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received. One commenter states that the proposed AD does
not apply to its fleet.
Request To Change Certain Terminology
One commenter states that the terminology throughout the proposed
AD which reads, ``cargo door frame(s)'' should be changed to ``cargo
doorway frames.'' The commenter notes that the structures requiring the
inspections are the cutout fuselage frames of the cargo door and not
the cargo door frames. The commenter adds that the term ``cargo
doorway,'' as specified in Boeing Alert Service Bulletin 757-53A0080,
dated February 3, 2000 (referenced in the proposed AD as the
appropriate source of service information for accomplishment of the
actions), is a better description.
We agree with the commenter in that the description of the frames
of the cargo door should be clarified. We have changed the description
throughout this final rule to read, ``cargo doorway.''
Explanation of Editorial Change
We have changed the service bulletin citation throughout this final
rule to exclude the Evaluation Form. (The form is intended to be
completed by operators and submitted to the
[[Page 71811]]
manufacturer to provide input on the quality of the service bulletin;
however, this AD does not include such a requirement.)
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the change previously
described. The FAA has determined that this change will neither
increase the economic burden on any operator nor increase the scope of
the AD.
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 identified in this AD. Once this
modification is developed, approved, and available, the FAA may
consider further rulemaking.
Cost Impact
There are approximately 57 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 28 airplanes of U.S. registry
will be affected by this AD.
For all airplanes: It will take approximately 3 work hours per
airplane to do the high frequency eddy current and detailed
inspections, at an average labor rate of $60 per work hour. Based on
these figures, the cost impact of the inspections required by this AD
on U.S. operators is estimated to be $5,040, or $180 per airplane, per
inspection cycle.
For Group 3 airplanes: It will take approximately 1 work hour per
airplane to do the additional detailed inspection, at an average labor
rate of $60 per work hour. Based on these figures, the cost impact of
this required inspection on U.S. operators is estimated to be $60 per
airplane, per inspection cycle.
The cost impact figures discussed above are 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:
2002-24-02 Boeing: Amendment 39-12967. Docket 2001-NM-192-AD.
Applicability: Model 757-200 series airplanes, line numbers 1
through 57 inclusive, 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 (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 find and fix fatigue cracking of the cargo doorway frames,
which could lead to rapid depressurization of the airplane and
result in reduced structural integrity of the cargo doorway,
accomplish the following:
Repetitive Inspections
(a) Before the accumulation of 22,000 total flight cycles or
within 500 flight cycles after the effective date of this AD,
whichever is later: Do the applicable inspections specified in
paragraphs (a)(1) and (a)(2) of this AD, per Boeing Alert Service
Bulletin 757-53A0080, excluding Evaluation Form, dated February 3,
2000.
(1) For all airplanes: Do detailed and high frequency eddy
current (HFEC) inspections for cracking of the doorway frames of the
number 1 and 2 cargo doors (includes the frame webs, frame inner and
outer chords, bear strap, and skin panels between the upper and
lower sills of the cargo doorway). Repeat the detailed inspections
every 3,000 flight cycles, and the HFEC inspections every 12,000
flight cycles.
(2) For Group 3 airplanes: Do a detailed inspection for cracking
of the doorway frame of the number 3 cargo door. Repeat the
inspection every 3,000 flight cycles.
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.''
Repair
(b) Before further flight, repair any cracking found in the
frame webs, per Boeing Alert Service Bulletin 757-53A0080, excluding
Evaluation Form, dated February 3, 2000. If any cracking is found in
any other area and the service bulletin specifies to contact Boeing
for disposition of those repairs, 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.
Note 3: There is no terminating action currently available for
the repetitive inspections required by this AD.
Alternative Methods of Compliance
(c) An alternative method of compliance or adjustment of the
compliance time that
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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 4: 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 per Boeing Alert Service Bulletin 757-53A0080,
excluding Evaluation Form, dated February 3, 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 January 7, 2003.
Issued in Renton, Washington, on November 20, 2002.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 02-30342 Filed 12-2-02; 8:45 am]
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