[Federal Register Volume 67, Number 232 (Tuesday, December 3, 2002)]
[Rules and Regulations]
[Pages 71808-71810]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-30344]


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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: 
[email protected]. 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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