[Federal Register Volume 67, Number 168 (Thursday, August 29, 2002)]
[Proposed Rules]
[Pages 55365-55368]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-22004]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-56-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 and -11F 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain McDonnell Douglas 
Model MD-11 and -11F airplanes, that currently requires a one-time 
detailed inspection to detect discrepancies of all electrical wiring 
installations in various areas of the airplane; and corrective actions, 
if necessary. This action would require another identical inspection in 
additional fuselage stations, and corrective actions, if necessary. 
This proposal is prompted by a report from the airplane manufacturer 
that it failed to include 41 inches of fuselage in the previously 
required inspection. The actions specified by the proposed AD are 
intended to prevent electrical arcing and/or heat damaged wires due to 
improper wire installations during manufacture and/or maintenance of 
the airplane, and consequent fire and smoke in various areas of the 
airplane.

DATES: Comments must be received by October 15, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-56-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. 2001-NM-56-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 the proposed rule 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.

FOR FURTHER INFORMATION CONTACT: Technical Information: Brett Portwood, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130L, FAA, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California 90712-4137; telephone (562) 627-5350; fax (562) 
627-5210.
    Other Information: Sandi Carli, Airworthiness Directive Technical 
Writer/Editor; telephone (425) 227-1120, 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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    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.

[[Page 55366]]

     For each issue, state what specific change to the proposed 
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 proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-56-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2001-NM-56-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On November 22, 2000, the FAA issued AD 2000-24-15, amendment 39-
12022 (65 FR 75620, December 4, 2000), applicable to certain McDonnell 
Douglas Model MD-11 airplanes, to require a one-time detailed 
inspection to detect discrepancies of all electrical wiring 
installations in various areas of the airplane, and corrective actions, 
if necessary. That action was prompted by incidents of damaged wire 
insulation and chafed wires in various areas. The requirements of that 
AD are intended to prevent electrical arcing and/or heat damaged wires 
due to improper wire installations during manufacture and/or 
maintenance of the airplane, and consequent fire and smoke in various 
areas of the airplane.
    The incident that prompted AD 2000-24-15 is not considered to be 
related to an accident that occurred off the coast of Nova Scotia 
involving a McDonnell Douglas Model MD-11 airplane. The cause of that 
accident is still under investigation.

Other Related Rulemaking

    The FAA, in conjunction with Boeing and operators of Model MD-11 
and -11F airplanes, is continuing to review all aspects of the service 
history of those airplanes to identify potential unsafe conditions and 
to take appropriate corrective actions. This proposed airworthiness 
directive (AD) is one of a series of actions identified during that 
process. The process is continuing and the FAA may consider additional 
rulemaking actions as further results of the review become available.

Actions Since Issuance of Previous Rule

    Since the issuance of AD 2000-24-15, the airplane manufacturer has 
informed the FAA that it failed to include 41 inches of fuselage in the 
inspection and corrective procedures of McDonnell Douglas Service 
Bulletin MD11-24-165, dated April 4, 2000, and Boeing Service Bulletin 
MD11-24-165, Revision 01, including Appendix, dated November 6, 2000 
(which are referenced in AD 2000-24-15 as appropriate sources of 
service information). This additional area is subject to the identified 
unsafe condition of AD 2000-24-15.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Service Bulletin MD11-24-
165, Revision 02, including Appendix, dated March 8, 2001. The 
procedures in Revision 02 of the service bulletin are essentially 
identical to those in the original version and Revision 01 of the 
service bulletin. The only relevant change is to the affected fuselage 
stations, which now include an additional 41 inches of fuselage to be 
inspected. Accomplishment of the actions specified in the service 
bulletin is intended to adequately address the identified unsafe 
condition.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would supersede AD 2000-24-15 to continue to require a one-
time detailed inspection to detect discrepancies of all electrical 
wiring installations in various areas of the airplane; and corrective 
actions, if necessary. The proposed AD also would require another 
identical inspection in additional fuselage stations, and corrective 
actions, if necessary. These additional actions would be required to be 
accomplished in accordance with Boeing Service Bulletin MD11-24-165, 
Revision 02, including Appendix, dated March 8, 2001, described 
previously.

Explanation of Change to Applicability

    The FAA finds that Model MD-11F airplanes are not specifically 
identified by model in the applicability of AD 2000-24-15; however, 
they are identified by manufacturer's fuselage numbers. Therefore, the 
FAA has revised the applicability of this proposed AD to include Model 
MD-11F airplanes in addition to Model MD-11 airplanes, and to identify 
model designations as published in the most recent type certificate 
data sheet for the affected models.

Explanation of Certain Previously Required Requirements

    As discussed in the preamble of notice of proposed rulemaking 
(NPRM) for AD 2000-24-15, the Accomplishment Instructions of the 
service bulletins referenced in that AD do NOT provide instructions for 
accomplishing corrective actions for certain discrepancies that are 
detected. Therefore, the FAA finds that the following corrective 
actions specified in paragraphs (c) and (d) of AD 2000-24-15, which 
have been retained and redesignated as paragraphs (d) and (e) in this 
proposed AD, must be accomplished, if necessary, to address the 
identified unsafe condition of the proposed AD:
     If no gap between the wire bundle and blanket can be seen 
when pressure is applied to the blanket, before further flight, 
reposition wires or clamping so that a gap can been seen when pressure 
is applied to the blanket.
     If any screw terminal of the flag lug bus bar is loose, 
before further flight, retorque to 10 to 11 inch-pounds.
    Operators should note that Boeing Service Bulletin MD11-24-165, 
Revision 02, including Appendix, dated March 8, 2001 (described 
previously), does contain these corrective actions.

Explanation of Change in Terminology

    The FAA has changed all references to a ``detailed visual 
inspection'' in the existing AD to ``detailed inspection'' in this 
proposed AD.

Cost Impact

    There are approximately 182 Model MD-11 and -11F airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 60 
airplanes of U.S. registry would be affected by this proposed AD.
    Each of the six inspections required by paragraphs (a)(1) through 
(a)(6) of this proposed AD, which are currently required by AD 2000-24-
15, approximately 10 work hours per airplane to accomplish, at an 
average labor rate of $60 per work hour. Based on these figures, the 
cost impact of these currently required actions on U.S. operators is 
estimated to be $216,000, or $3,600 per airplane.

[[Page 55367]]

    The inspection required by paragraph (a)(7) of this proposed AD, 
which is currently required by AD 2000-24-15, takes approximately 5 
work hours per airplane to accomplish, at an average labor rate of $60 
per work hour. Based on these figures, the cost impact of this 
currently required action on U.S. operators is estimated to be $18,000, 
or $300 per airplane.
    The inspection required by paragraph (a)(8) of this proposed AD, 
which is currently required by AD 2000-24-15, takes approximately 12 
work hours per airplane to accomplish, at an average labor rate of $60 
per work hour. Based on these figures, the cost impact of this 
currently required action on U.S. operators is estimated to be $43,200, 
or $720 per airplane.
    The new inspection required by paragraph (b) of this proposed AD 
would take approximately 1 work hour per airplane to accomplish, at an 
average labor rate of $60 per work hour. Based on these figures, the 
cost impact of this proposed inspection of this AD on U.S. operators is 
estimated to be $3,600, or $60 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the current or proposed 
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. However, the FAA has been 
advised that manufacturer warranty remedies are available for labor 
costs associated with accomplishing the actions required by this 
proposed AD. Therefore, the future economic cost impact of this rule on 
U.S. operators may be less than the cost impact figure indicated above.

Regulatory Impact

    The regulations proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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 removing amendment 39-12022 (65 FR 
75620, December 4, 2000), and by adding a new airworthiness directive 
(AD), to read as follows:

McDonnell Douglas: Docket 2001-NM-56-AD. Supersedes AD 2000-24-15, 
Amendment 39-12022.
    Applicability: Model MD-11 and -11F airplanes, manufacturer's 
fuselage numbers 0447 through 0449 inclusive, 0451 through 0464 
inclusive, 0466 through 0489 inclusive, 0491 through 0517 inclusive, 
0519 through 0552 inclusive, 0554 through 0556 inclusive, 0557, 0558 
through 0633 inclusive, and 0635; 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 (f)(1) 
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.

    Note 2: The FAA recommends that the actions required by this AD 
be accomplished immediately after accomplishing the replacement of 
metallized polyethyleneteraphthalate (MPET) insulation blankets, as 
required by AD 2000-11-02, amendment 39-11750 (65 FR 34341, May 26, 
2000).

    To prevent electrical arcing and/or heat damaged wires due to 
improper wire installations during manufacture and/or maintenance of 
the airplane, and consequent fire and smoke in various areas of the 
airplane, accomplish the following:

Restatement of Certain Requirements of AD 2000-24-15

One-Time Detailed Inspection

    (a) Within 5 years after January 8, 2001 (the effective date of 
AD 2000-24-15, amendment 39-12022), accomplish the actions specified 
in paragraphs (a)(1), (a)(2), (a)(3), (a)(4), (a)(5), (a)(6), 
(a)(7), and (a)(8) of this AD, as applicable.
    (1) For all airplanes: Perform a one-time detailed inspection to 
detect discrepancies of all electrical wiring installations in the 
center and aft cargo compartments from stations Y=1521.000 to 
Y=2007.000, in accordance with paragraph 3.B., ``Work 
Instructions,'' of the Accomplishment Instructions of McDonnell 
Douglas Service Bulletin MD11-24-171, dated April 4, 2000; or 
Revision 01, dated November 6, 2000.

    Note 3: 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.''

    (2) For all airplanes: Perform a one-time detailed inspection to 
detect discrepancies of all electrical wiring installations in the 
forward cargo compartment from stations Y=595.000 to Y=6-73.500, in 
accordance with the paragraph 3.B., ``Work Instructions,'' of the 
Accomplishment Instructions of McDonnell Douglas Service Bulletin 
MD11-24-170, dated April 12, 2000; or Revision 01, dated November 6, 
2000.
    (3) For all airplanes: Perform a one-time detailed inspection to 
detect discrepancies of all electrical wiring installations in the 
forward passenger compartment from stations Y=5-11.000 to 
Y=2007.000, in accordance with the paragraph 3.B., ``Work 
Instructions,'' of the Accomplishment Instructions of McDonnell 
Douglas Service Bulletin MD11-24-167, dated April 4, 2000; or Boeing 
Service Bulletin MD11-24-167, Revision 01, including Appendix 1, 
dated November 6, 2000.
    (4) For all airplanes: Perform a one-time detailed inspection to 
detect discrepancies of all electrical wiring installations in the 
forward passenger compartment from stations Y=756.000 to Y=1501.000, 
in accordance with the paragraph 3.B., ``Work Instructions,'' of the 
Accomplishment Instructions of McDonnell Douglas Service Bulletin 
MD11-24-165, dated April 4, 2000;

[[Page 55368]]

or Boeing Service Bulletin MD11-24-165, Revision 01, including 
Appendix, dated November 6, 2000, or Revision 02, including 
Appendix, dated March 8, 2001.
    (5) For all airplanes: Perform a one-time detailed inspection to 
detect discrepancies of all electrical wiring installations in the 
forward passenger compartment from stations Y=465.000 to Y=755.000, 
in accordance with the paragraph 3.B., ``Work Instructions,'' of the 
Accomplishment Instructions of McDonnell Douglas Service Bulletin 
MD11-24-163, dated April 4, 2000; or Boeing Service Bulletin MD11-
24-163, Revision 01, including Appendix 1, dated November 6, 2000.
    (6) For all airplanes: Perform a one-time detailed inspection to 
detect discrepancies of all electrical wiring installations in the 
flight compartment and forward drop ceilings areas from stations 
Y=275.000 to Y=464.000, in accordance with the paragraph 3.B., 
``Work Instructions,'' of the Accomplishment Instructions of 
McDonnell Douglas Service Bulletin MD11-24-188, dated April 28, 
2000; or Revision 01, dated November 6, 2000.
    (7) For airplanes having manufacturer's fuselage numbers 0447 
through 0449 inclusive, 0451 through 0464 inclusive, 0466 through 
0489 inclusive, 0491 through 0517 inclusive, 0519 through 0552 
inclusive, 0554 through 0556 inclusive, 0557, and 0558 through 0633 
inclusive: Perform a one-time detailed inspection to detect 
discrepancies of all electrical wiring installations in the center 
accessory compartment from stations Y=6-50.000 to Y=1179.000, in 
accordance with the paragraph 3.B., ``Work Instructions,'' of the 
Accomplishment Instructions of McDonnell Douglas Service Bulletin 
MD11-24-161, dated April 10, 2000; or Revision 01, dated November 6, 
2000.
    (8) For airplanes having manufacturer's fuselage numbers 0447 
through 0449 inclusive, 0451 through 0464 inclusive, 0466 through 
0489 inclusive, 0491 through 0517 inclusive, 0519 through 0552 
inclusive, 0554 through 0556 inclusive, 0557, and 0558 through 0633 
inclusive: Perform a one-time detailed inspection to detect 
discrepancies of all electrical wiring installations in the main 
avionics compartment from stations Y=275.000 to Y=464.000, in 
accordance with the paragraph 3.B., ``Work Instructions,'' of the 
Accomplishment Instructions of McDonnell Douglas Service Bulletin 
MD11-24-162, dated April 10, 2000; or Revision 01, dated November 6, 
2000.

New Actions Required by This AD

One-Time Detailed Inspection

    (b) For Group 2 airplanes identified in Boeing Service Bulletin 
MD11-24-165, Revision 02, including Appendix, dated March 8, 2001: 
Within 5 years after the effective date of this AD, perform a one-
time detailed inspection to detect discrepancies of all electrical 
wiring installations in the forward passenger compartment from 
stations Y=1501.000 to Y=5-10.000, in accordance with the paragraph 
3.B., ``Work Instructions,'' ``Group 2,'' of the Accomplishment 
Instructions of Boeing Service Bulletin MD11-24-165, Revision 02, 
dated March 8, 2001.

Corrective Action

    (c) If any discrepancy is detected during the inspection 
required by paragraphs (a)(1) through (a)(8) of this AD or paragraph 
(b) of this AD, before further flight, accomplish the applicable 
corrective action(s) in accordance with the Accomplishment 
Instructions of the following applicable service bulletins, except 
as provided in paragraphs (d) and (e) of this AD, as applicable:
    (1) McDonnell Douglas Service Bulletin MD11-24-171, dated April 
4, 2000; or Revision 01, dated November 6, 2000;
    (2) McDonnell Douglas Service Bulletin MD11-24-170, dated April 
12, 2000; or Revision 01, dated November 6, 2000;
    (3) McDonnell Douglas Service Bulletin MD11-24-167, dated April 
4, 2000;
    (4) Boeing Service Bulletin MD11-24-167, dated April 4, 2000, 
Revision 01, including Appendix, dated November 6, 2000;
    (5) McDonnell Douglas Service Bulletin MD11-24-165, dated April 
4, 2000;
    (6) Boeing Service Bulletin MD11-24-165, Revision 01, including 
Appendix, dated November 6, 2000;
    (7) McDonnell Douglas Service Bulletin MD11-24-163, dated April 
4, 2000;
    (8) Boeing Service Bulletin MD11-24-163, Revision 01, including 
Appendix 1, dated November 6, 2000;
    (9) McDonnell Douglas Service Bulletin MD11-24-188, dated April 
28, 2000; or Revision 01, dated November 6, 2000;
    (10) McDonnell Douglas Service Bulletin MD11-24-161, dated April 
10, 2000; or Revision 01, dated November 6, 2000; or
    (11) McDonnell Douglas Service Bulletin MD11-24-162, dated April 
10, 2000; or Revision 01, dated November 6, 2000.
    (12) Boeing Service Bulletin MD11-24-165, Revision 02, including 
Appendix, dated March 8, 2001.

    Note 4: Where there are differences between the AD and the 
referenced service bulletins, the AD prevails.

    (d) If no gap between the wire bundle and blanket can be seen 
where the wiring is routed over the structural frames when pressure 
is applied to the blanket, before further flight, reposition wires 
or clamps so that a gap can be seen when pressure is applied to the 
blanket.
    (e) If any screw terminal of the flag lug bus bar is loose, 
before further flight, retorque to 10 to 11 inch-pounds.

Alternative Methods of Compliance

    (f)(1) 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 Aircraft Certification 
Office (ACO), FAA. 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 5: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

    (2) Alternative methods of compliance, approved previously in 
accordance with AD 2000-24-15, amendment 39-12022, are approved as 
alternative methods of compliance with this AD.

Special Flight Permits

    (g) 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.

    Issued in Renton, Washington, on August 20, 2002.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-22004 Filed 8-28-02; 8:45 am]
BILLING CODE 4910-13-P