[Federal Register: December 3, 2002 (Volume 67, Number 232)]
[Rules and Regulations]
[Page 71808-71810]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr03de02-4]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-271-AD; Amendment 39-12970; AD 2002-24-05]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727 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 727 series airplanes. This action
requires detailed inspections to detect cracking and corrosion of the
upper chord of the rear spar of the wing; and repair, if necessary.
This action also requires detailed inspections to detect and
permanently repair any cracking that has been previously repaired by
stop-drilling. This action is necessary to prevent failure of the wing
and fuel leaks in the airplane due to stress corrosion cracking of the
upper chord of the rear spar. This action is intended to address the
identified unsafe condition.
DATES: Effective December 18, 2002.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 18, 2002.
Comments for inclusion in the Rules Docket must be received on or
before February 3, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2002-NM-271-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. 2002-NM-271-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: 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 has received reports of spanwise
stress corrosion cracking of the upper chord of the rear spar of the
wing between Wing Butt Line (WBL) 70.5 and the wing tip. Investigation
revealed that some cracks were up to 14 inches long. Further, one of
the cracks was almost long enough to jeopardize the residual strength
capability of the upper chord of the rear spar. Such cracking of the
upper chord of the rear spar of the wing, if not corrected, could
result in structural failure of the wing and fuel leaks in the
airplane.
Explanation of Relevant Service Information
The FAA has reviewed and approved Boeing Alert Service Bulletin
(ASB) 727-57A0145, revision 2, dated October 24, 2002. That ASB
describes procedures for performing repetitive external detailed
inspections on airplanes specified as ``Group 1'' to detect cracking
and corrosion of the upper chord of the rear spar of the wing, and
repair, if necessary. The ASB also describes procedures for detecting
and permanently repairing any cracking that was previously repaired by
stop-drilling. Additionally, the ASB describes procedures to perform
high-frequency eddy current inspections (HFEC) on ``Group 1'' airplanes
to detect cracking and corrosion of the upper chord of the rear spar
and corrective action. Further, the ASB describes procedures to perform
external detailed inspections and HFEC inspections on ``Group 1''
airplanes to detect cracking and corrosion of other areas such as the
lower chord of the rear spar and the upper and lower chords of the
front spar. In addition, the ASB describes procedures for certain other
airplanes specified as ``Group 2'' airplanes that include external
detailed inspections and HFEC inspections of various areas to detect
cracking and corrosion; and repair, if necessary. The ASB also
describes repair procedures for minor surface defects, corrosion, and
cracking.
[[Page 71809]]
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 is
being issued to prevent failure of the wing and fuel leaks in the
airplane due to stress corrosion cracking of the upper chord of the
rear spar. This AD requires the following actions for airplanes
designated as ``Group 1'' in Boeing Alert Service Bulletin 727-57A0145,
revision 2, dated October 24, 2002:
[sbull] Repetitive external detailed inspections to detect cracking
and corrosion of the upper chord of the rear spar of the wing,
[sbull] Repair of cracking and corrosion,
[sbull] External detailed inspections to detect any cracking that
has been previously repaired by stop-drilling, and
[sbull] Permanent repair of any previously stop-drilled cracking.
Clarification of Certain Repair Conditions
Operators should note that, although the alert service bulletin
specifies that the manufacturer may be contacted for disposition of
certain repair conditions, this AD requires that those conditions 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
FAA to make such findings.
Interim Action
The actions required by this AD are considered to be interim
action. The FAA is currently considering requiring additional actions
specified in the alert service bulletin. However, the planned
compliance time for the implementation of those actions is sufficiently
long so that notice and opportunity for prior public comment will be
practicable.
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-271-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:
2002-24-05 Boeing: Amendment 39-12970. Docket 2002-NM-271-AD.
Applicability: Model 727 series airplanes, serial numbers 1
through 1832 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 (b) 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 prevent structural failure of the wing and fuel leaks in the
airplane due to stress corrosion cracking of the upper chord of the
rear spar, accomplish the following:
Inspection and Repair
(a) For airplanes specified as ``Group 1'' airplanes in Boeing
Alert Service Bulletin 727-57A0145, revision 2, dated October 24,
2002: Within 20 years after the date of manufacture or within 90
days after the effective date of this AD, whichever occurs
[[Page 71810]]
later, perform an external detailed inspection for cracking,
corrosion, and existing stop-drilled repairs of cracking in the
upper chord on the rear spar from Wing Butt Line (WBL) 70.5 through
WBL 249.3, per Boeing Alert Service Bulletin 727-57A0145, revision
2, paragraph 3.B, ``Work Instructions,'' part 1, dated October 24,
2002. Thereafter, repeat the inspection at intervals not to exceed 2
years.
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) If no cracking, corrosion, or existing stop-drilled repairs
of previous cracking is detected during any inspection required by
this AD, repeat the inspection at intervals not to exceed 2 years.
(2) If any existing stop-drilled repairs of previous cracking
are detected during any inspection required by this AD, before
further flight, permanently repair the cracking per the alert
service bulletin.
(3) If any cracking or corrosion is detected during any
inspection required by this AD that is within the limits specified
in the alert service bulletin, before further flight, repair per the
alert service bulletin.
(4) If any cracking or corrosion is detected during any
inspection required by this AD that exceeds the limits specified in
the alert service bulletin, and the 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 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.
Alternative Methods of Compliance
(b) 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
(c) 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
(d) Except as specified in paragraph (a)(4) of this AD, the
actions shall be done in accordance with Boeing Alert Service
Bulletin 727-57A0145, revision 2, dated October 24, 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,
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
(e) This amendment becomes effective on December 18, 2002.
Issued in Renton, Washington, on November 20, 2002.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 02-30344 Filed 12-2-02; 8:45 am]
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