[Federal Register Volume 67, Number 138 (Thursday, July 18, 2002)]
[Rules and Regulations]
[Pages 47254-47256]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-18024]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-168-AD; Amendment 39-12803; AD 2002-14-03]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 and -11F 
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 McDonnell Douglas Model MD-11 and 11F 
airplanes. This action requires a one-time inspection to detect loose 
preload-indicating (PLI) washers or cracked or corroded nuts of the 
lower bolts of the inboard flap outboard hinge, and replacement with 
new parts if necessary. This action is necessary to detect and correct 
loose PLI washers or cracked or corroded nuts of the lower bolts of the 
inboard flap outboard hinge, which could result in separation of the 
inboard flap outboard hinge from the wing structure and consequent 
reduced controllability of the airplane.

DATES: Effective August 2, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 2, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before September 16, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-168-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-168-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 Aircraft Group, Long Beach Division, 3855 Lakewood 
Boulevard, Long Beach, California 90846, Attention: Data and Service 
Management, Dept. C1-L5A (D800-0024). This information may be examined 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington; or at the FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Technical Information: Ronald Atmur, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles 
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, 
California 90712-4137; telephone (562) 627-5224; fax (562) 627-5210.
    Other Information: Sandi Carli, Airworthiness Directive Technical 
Editor/Writer; telephone (425) 687-4243, fax (425) 227-1232. Questions 
or comments may also be sent via the Internet using the following 
address: [email protected]. Questions or comments sent via the 
Internet as attached electronic files must be formatted in Microsoft 
Word 97 for Windows or ASCII text.

SUPPLEMENTARY INFORMATION: The FAA has received a report of an incident 
involving a McDonnell Douglas Model MD-11 airplane on which a loud bang 
was heard when the airplane was on approach with gear down and flaps 
set at 50 degrees. The airplane shuddered and then rolled left. The 
flightcrew applied full right-hand aileron to level the wings, missed 
the approach, and declared an emergency. During landing, the tail of 
the airplane scraped the runway. Reports indicate that the left-hand 
inboard flap outboard hinge pulled away from the wing structure where 
it attaches with two upper and two lower bolts. It was determined that 
the lower bolts likely failed first. This condition, if not corrected, 
could result in reduced controllability of the airplane.
    The design of the subject area of the airplane is the same on Model 
DC-10 and MD-11 airplanes. The DC-10 is subjected to lower loads and is 
less likely to experience this failure. However, Model MD-11 airplanes 
experience higher loads. In addition, current parts availability only 
supports the MD-11 fleet. In light of these factors, we have determined 
that it is appropriate at this time to address the airplane model that 
has higher loads and has experienced the failure. After additional 
investigation into the cause of the incident on Model MD-11 airplanes, 
we may consider related rulemaking for Model DC-10 airplanes.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
MD11-57A067, including Appendices A and B, dated July 10, 2002, which 
describes various procedures for different groups of airplanes, based 
on the composition of the nuts on the lower bolts of the inboard flap 
outboard hinge.
    Group 1 airplanes have alloy steel nuts, and Group 2 airplanes have 
Inconel nuts. The procedures for these airplane groups include removing 
sealant from the head and nut sides of both bolt assemblies, using a 
wiggle tool to detect looseness of the preload-indicating (PLI) 
washers, and visually inspecting the nut for corrosion and cracking. 
Based on the results of the inspection, follow-on and corrective 
actions include doing a magnetic particle inspection of the bolt to 
detect cracking and corrosion, replacing discrepant parts with new 
Inconel and/or alloy steel bolts and nuts and new PLI washers, and 
applying sealant.

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 detect and correct loose PLI washers or cracked or 
corroded nuts of the lower bolts of the inboard flap outboard hinge, 
which could result in separation of the inboard flap outboard hinge 
from the wing structure and consequent reduced controllability of the 
airplane. This AD requires a one-time inspection to detect loose PLI 
washers or cracked or corroded nuts of the lower bolts of the inboard 
flap outboard hinge, and replacement with new parts if necessary. This 
AD also requires that operators report results of inspection findings 
to the FAA.

Differences Between AD and Service Bulletin

    The alert service bulletin specifies that operators may test for 
looseness of the PLI washers by use of a wiggle tool, ``or 
equivalent.'' However, this AD requires that any alternative to the 
wiggle-tool test be accomplished in accordance with a method approved 
by the FAA. Use of an equivalent tool or test procedure is allowed only 
if approved as an alternative method of compliance in accordance with 
the

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requirements of paragraph (e) of this AD.
    Further, although the alert service bulletin specifies that the 
manufacturer may be contacted for disposition of ``additional 
examination recommendations,'' this AD requires that such actions be 
accomplished in accordance with a method approved by the FAA.

Interim Action

    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking. 
Because the cause of the unsafe condition is not currently known, the 
intent of the required inspection reports is to enable the FAA to 
determine the extent of the problem in the affected fleet. Based on the 
results of these reports, further corrective action may be warranted.

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 2002-NM-168-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:

2002-14-03  McDonnell Douglas: Amendment 39-12803. Docket 2002-NM-
168-AD.

    Applicability: Model MD-11 and -11F airplanes listed as Group 1 
or Group 2 airplanes in Boeing Alert Service Bulletin MD11-57A067, 
including Appendices A and B, dated July 10, 2002; 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 (e) 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 loose preload-indicating (PLI) washers or 
cracked or corroded nuts of the lower bolts of the inboard flap 
outboard hinge, which could result in separation of the inboard flap 
outboard hinge from the wing structure and consequent reduced 
controllability of the airplane, accomplish the following:

Inspection

    (a) At the applicable time specified in paragraph (a)(1) or 
(a)(2) of this AD, do a detailed inspection (including removing 
sealant from the head and nut sides of both bolt assemblies) of the 
nuts and PLI washers of the lower bolts of the inboard flap outboard 
hinge to detect discrepancies (including loose PLI washers or 
cracked or corroded nuts, as applicable), in accordance with Boeing 
Alert Service Bulletin MD11-57A067, including Appendices A and B, 
dated July 10, 2002, except as required by paragraphs (b) and (c) of 
this AD. Before further flight thereafter, do applicable follow-on 
and corrective actions (including performing a magnetic particle 
inspection of the bolt to detect cracking and corrosion, replacing 
discrepant parts with new Inconel and/or alloy steel bolts and nuts 
and new PLI washers, and applying sealant, as applicable); and, 
within 600 flight cycles, replace discrepant bolts, nuts, and 
washers with new parts, as applicable; in accordance with the alert 
service bulletin.
    (1) For Group 1 airplanes: Inspect within 30 days after the 
effective date of this AD.

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    (2) For Group 2 airplanes: Inspect within 60 days after the 
effective date of this AD.

    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.''

Exceptions to Paragraph (a) Requirements

    (b) Where Boeing Alert Service Bulletin MD11-57A067, including 
Appendices A and B, dated July 10, 2002, specifies that testing for 
looseness of the PLI washers may be accomplished by the use of a 
wiggle tool, ``or equivalent'': Either the wiggle tool must be used, 
or the test must be accomplished in accordance with a method 
approved by the Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA.
    (c) Where Boeing Alert Service Bulletin MD11-57A067, including 
Appendices A and B, dated July 10, 2002, specifies to contact Boeing 
for ``additional examination recommendations'': Before further 
flight, these actions, if accomplished, must be performed in 
accordance with a method approved by the Manager, Los Angeles ACO. 
For such a method to be approved by the Manager, Los Angeles ACO, as 
required by this paragraph, the Manager's approval letter must 
specifically refer to this AD.

Reporting Requirement

    (d) At the applicable time specified in paragraph (d)(1) or 
(d)(2) of this AD: Send a report of the results (both positive and 
negative) of the inspection nuts and PLI washers of the lower bolts 
of the inboard flap outboard hinge to the Manager, Los Angeles ACO, 
FAA, 3960 Paramount Boulevard, Lakewood, CA 90712-4137, fax (562) 
627-5210. The report must include the factory serial number of the 
airplane; inspection results for all four bolts; a description of 
any discrepancies found; the part numbers for the bolt, nut, and PLI 
washers; and the total number of landings and flight hours 
accumulated on the airplane. Information collection requirements 
contained in this AD have been approved by the Office of Management 
and Budget (OMB) under the provisions of the Paperwork Reduction Act 
of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control 
Number 2120-0056.
    (1) For airplanes on which the inspection is accomplished after 
the effective date of this AD: Submit the report within 10 days 
after performing the inspection required by paragraph (a) of this 
AD.
    (2) For airplanes on which the inspection has been accomplished 
prior to the effective date of this AD: Submit the report within 10 
days after the effective date of this AD.

Alternative Methods of Compliance

    (e) 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, Los Angeles ACO. Operators shall 
submit their requests through an appropriate FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Los Angeles ACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

Special Flight Permits

    (f) Special flight permits may be issued in accordance with 
Secs. 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

    (g) Except as required by paragraphs (b) and (c) of this AD: The 
actions must be done in accordance with Boeing Alert Service 
Bulletin MD11-57A067, including Appendices A and B, dated July 10, 
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 Aircraft 
Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, 
California 90846, Attention: Data and Service Management, Dept. C1-
L5A (D800-0024). Copies may be inspected at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 
at the FAA, Los Angeles Aircraft Certification Office, 3960 
Paramount Boulevard, Lakewood, California; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

Effective Date

    (h) This amendment becomes effective on August 2, 2002.

    Issued in Renton, Washington, on July 10, 2002.
Vi Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-18024 Filed 7-17-02; 8:45 am]
BILLING CODE 4910-13-P