[Federal Register Volume 65, Number 145 (Thursday, July 27, 2000)]
[Proposed Rules]
[Pages 46223-46226]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-18402]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-38-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 Series 
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 series airplanes, that currently requires deactivation of 
the forward and center cargo control units (CCU). That AD was prompted 
by a report of failure of a CCU, which produced overheating of the 
electrical pins inside the CCU; the subsequent release of hot gases and 
flames ignited an adjacent insulation blanket. This action would 
require, among other actions, a general visual inspection to verify 
that all six external connectors of suspect CCU's have a certain part 
number stamped on the connector bodies on all CCU assemblies, and 
follow-on actions, which would constitute terminating action for the 
deactiviation requirements. The actions specified by the proposed AD 
are intended to prevent overheating of the electrical pins inside the 
CCU's and subsequent release of hot gases and flames, which could 
result in smoke and fire in the cargo compartment.

DATES: Comments must be received by September 11, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket
    No. 2000-NM-38-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056. 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. 2000-NM-38-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: 
Technical Publications Business Administration, Dept. C1-L51 (2-60). 
This information may be examined at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, 
Transport Airplane Directorate, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California.

FOR FURTHER INFORMATION CONTACT: Brett Portwood, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, Transport Airplane 
Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount 
Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5350; 
fax (562) 627-5210.

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 notice 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.
     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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NM-38-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. 2000-NM-38-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On April 12, 2000, the FAA issued AD 2000-08-03, amendment 39-11689 
(65 FR 21134, April 20, 2000), applicable to certain McDonnell Douglas 
Model MD-11 series airplanes, to require deactivation of the forward 
and center cargo control units (CCU).
    That action was prompted by a report of failure of a CCU, which 
produced overheating of the electrical pins inside the CCU; the 
subsequent release of hot gases and flames ignited an adjacent 
insulation blanket. The requirements of that AD are intended to prevent 
overheating of the electrical pins inside the CCU's and subsequent 
release of hot gases and flames, which could result in smoke and fire 
in the cargo compartment.

Actions Since Issuance of Previous Rule

    In the preamble of AD 2000-08-03, the FAA indicated that the 
actions required by that AD were considered ``interim action'' and that 
further rulemaking was being considered to require modification of the 
CCU assembly, which would constitute terminating action for the 
requirements of AD 2000-08-03. The FAA now has determined that further 
rulemaking is indeed necessary, and this proposed AD follows from that 
determination.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
MD11-25A253, dated March 10, 2000. The service bulletin describes 
procedures for a general visual inspection to verify that all six 
external connectors of the CCU's have a certain part number stamped on 
the connector bodies on all TRW Aeronautical Systems, Lucas Aerospace, 
CCU assemblies; and follow-on actions. The follow-on actions include:

[[Page 46224]]

Returning any discrepant connector to the manufacturer; modifying the 
rear cover (40) of the CCU assembly [including aligning the center hole 
of the insulator with the center hole on the rear cover (40); ensuring 
that the top edge of the insulator is parallel to the top edge of the 
rear cover]; and reidentifying the CCU; as applicable. Accomplishment 
of the actions specified in the service bulletin is intended to 
adequately address the identified unsafe condition.
    Boeing Alert Service Bulletin MD11-25A253 references TRW 
Aeronautical Systems, Lucas Aerospace Alert Service Bulletin 462650-25-
A01, dated March 10, 2000, as an additional source of service 
information to accomplish the inspection and follow-on actions 
described above.

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 2000-08-03 to continue to require 
deactivation of the forward and center CCU's, until accomplishment of 
the actions specified in Boeing Alert Service Bulletin MD11-25A253 
described previously. The proposed AD also would require an inspection 
to determine the part number of the CCU's, and accomplishment of the 
actions specified in the Boeing service bulletin described previously, 
if necessary, except as discussed below.

Differences Between the Proposed AD and Relevant Service Bulletin

    Although Boeing Alert Service Bulletin MD11-25A253 recommends 
accomplishing the general visual inspection within 15 days (from issue 
date of the service bulletin), the FAA has determined that an interval 
of 90 days would address the identified unsafe condition in a timely 
manner. Because operators have already accomplished the interim 
requirements (i.e., deactivation of the discrepant CCU's) of AD 2000-
08-03 (which includes the requirements of AD 2000-05-01), the FAA finds 
that the safety risk of the affected airplanes has been reduced. 
Therefore, the FAA has determined that a 90-day compliance time for 
initiating the required inspection to be warranted, in that it 
represents an appropriate interval of time allowable for affected 
airplanes to continue to operate without compromising safety.
    Boeing Alert Service Bulletin MD11-25A253 (which, as described 
previously, references TRW Aeronautical Systems, Lucas Aerospace Alert 
Service Bulletin 462650-25-A01 as an additional source of service 
information) recommends that certain discrepant CCU's be returned to 
the manufacturer; however, it does not describe any further procedures 
to correct the discrepancy. Therefore, this proposed AD requires 
replacement of the discrepant CCU with a CCU that has one of the 
following part numbers (P/N): 462650-21, 462650-22, or 462650-23.
    Since the issuance of Boeing Alert Service Bulletin MD11-25A253, 
Lucas has incorporated a design change to the CCU's. Lucas incorporated 
this design change in CCU's having P/N 462650-21, 462650-22, and 
462650-23. The FAA finds that these CCU's are not subject to the 
identified unsafe condition of this AD. Therefore, in addition to the 
procedures in the referenced service bulletin, this proposed AD would 
require a general visual inspection to determine the part number of the 
CCU's. Depending on the inspection results, the proposed AD would then 
require a general visual inspection to verify that all six external 
connectors of the suspect CCU have a certain part number stamped on the 
connector bodies on all CCU assemblies, as described in the referenced 
service bulletin, and follow-on actions.

Cost Impact

    There are approximately 104 Model MD-11 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 20 
airplanes of U.S. registry would be affected by this proposed AD.
    The actions that are currently required by AD 2000-08-03 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 the currently required actions on U.S. operators is estimated 
to be $1,200, or $60 per airplane.
    The new inspection that is proposed in this AD action 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 the inspection proposed by this AD on U.S. operators is 
estimated to be $1,200, or $60 per airplane.
    Should an operator be required to accomplish the new modification 
that is proposed in this AD action, it would take approximately 1 work 
hour per airplane to accomplish, at an average labor rate of $60 per 
work hour. Required parts would be supplied by the manufacturer of the 
CCU at no cost to the operators. Based on these figures, the cost 
impact of the modification proposed by this AD on U.S. operators is 
estimated to be $60 per airplane.
    Should an operator be required to accomplish the new replacement 
that is proposed in this AD action, it would take approximately 1 work 
hour per airplane to accomplish, at an average labor rate of $60 per 
work hour. Required parts would be supplied by the manufacturer of the 
CCU at no cost to the operators. Based on these figures, the cost 
impact of the replacement proposed by this AD on U.S. operators is 
estimated to be $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.

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:

[[Page 46225]]


    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-11689 (65 FR 
21134, April 20, 2000), and by adding a new airworthiness directive 
(AD), to read as follows:

McDonnell Doulgas: Docket 2000-NM-38-AD. Supersedes AD 2000-08-03, 
Amendment 39-11689.

    Applicability: Model MD-11 series airplanes, certificated in any 
category, having the serial numbers listed below.

 
 
 
                                                Group 1 Airplane
 
 48565             48566              48533              48549              48470              48406
48504              48602              48603              48571              48439              48605
48572              48471              48573              48600              48601              48633
48513              48574              48575              48542              48543              48576
48415              48631              48544              48632              48577              48545
48578              48546              48743              48744              48747              48748
48745              48746              48749              48579              48766              48768
48767              48769              48754              48623              48770              48753
48773              48774              48755              48758                     48775-48779 (inclusive)
48624              48756              48780              48532
 
                                                 Group 2 Airplane
48555              48556              48581              48630              48557              48539
48558              48559              48616              48560              48617              48618
48561              48629              48562              48563              48757              48540
48564              48634              48541              48798                     48781-48792 (inclusive)
48794              48799              48801              48800                     48802-48806 (inclusive)
 


    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) 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 overheating of the electrical pins inside the cargo 
control units (CCU) and subsequent release of hot gases and flames, 
which could result in smoke and fire in the cargo compartment, 
accomplish the following:

Restatement of Requirements of AD 2000-05-01: Deactivation

    (a) For Group 1 airplanes having serial numbers other than that 
identified in paragraph (c) of this AD: Within 15 days after March 
20, 2000 (the effective date of AD 2000-05-01, amendment 39-11610), 
deactivate the forward and center CCU's in accordance with the 
following procedures:
    (1) Remove the access panel to the forward cargo compartment CCU 
circuit breaker panel located at fuselage station 1009.300 (right 
side looking aft). Pull and collar the following circuit breakers:

      B1-506         B1-489         B1-488         B1-487        B1-486
      B1-485         B1-480         B1-481         B1-498        B1-482
      B1-500         B1-495         B1-499         B1-490
 

    (2) Remove the access panel to the center cargo compartment CCU 
circuit breaker panel located at fuselage station 1701.000 (right 
side looking aft). Pull and collar the following circuit breakers:

      B1-552         B1-762         B1-761         B1-760        B1-759
      B1-758         B1-518         B1-519         B1-751        B1-520
      B1-753         B1-764         B1-752         B1-763
 

    (b) For Group 2 airplanes having serial numbers other than that 
identified in paragraph (c) of this AD: Within 15 days after March 
20, 2000, deactivate the forward and center CCU's in accordance with 
the following procedures:
    (1) Remove the access panel to the forward cargo compartment CCU 
circuit breaker panel located at fuselage station 1009.300 (right 
side looking aft). Pull and collar the following circuit breakers:

      B1-506         B1-489         B1-488         B1-487        B1-486
      B1-485         B1-480         B1-481         B1-498        B1-482
      B1-500         B1-495         B1-499         B1-490
 

    (2) Remove the access panel to the center cargo compartment CCU 
circuit breaker panel located at fuselage station 1701.000 (right 
side looking aft). Pull and collar the following circuit breakers:

      B1-552         B1-762         B1-761         B1-760        B1-759
      B1-758         B1-518         B1-519         B1-751        B1-520
      B1-753         B1-764         B1-752
 


[[Page 46226]]

Restatement of Requirements of AD 2000-08-03: Deactivation

    (c) For Group 1 airplane, serial number 48769, and for Group 2 
airplane, serial number 48563: Within 15 days after May 5, 2000 (the 
effective date of AD 2000-08-03, amendment 39-11689), accomplish the 
actions specified in either paragraph (a) or (b) of this AD, as 
applicable.

New Requirements of This AD: Inspection and Modification/
Reidentification, If Necessary

    (d) For Group 1 and Group 2 airplanes: Within 90 days after the 
effective date of this AD, perform an inspection to determine the 
part number of the CCU's.
    (1) If both CCU's have part number (P/N) 462650-21, 462650-22, 
or 462650-23, the deactivation specified in paragraphs (a), (b), and 
(c) of this AD is no longer required, and the CCU's may be 
reactivated.
    (2) If any CCU has a part number (P/N) other than 462650-21, 
462650-22, or 462650-23, within 90 days after the effective date of 
this AD, perform a general visual inspection to verify that all six 
external connectors of the CCU have P/N M83723/71XXXXXX or P/N 
M83723/72XXXXXX stamped on the connector bodies on all TRW 
Aeronautical Systems, Lucas Aerospace, CCU assemblies, in accordance 
with Boeing Alert Service Bulletin MD11-25A253, dated March 10, 
2000.

    Note 2: McDonnell Douglas Service Bulletin MD11-25A253, dated 
March 10, 2000, references TRW Aeronautical Systems, Lucas Aerospace 
Alert Service Bulletin 462650-25-A01, dated March 10, 2000, as an 
additional source of service information to accomplish the 
inspection described above and corrective actions described below.
    (i) If any connector has a P/N other than M83723/71XXXXXX or 
M83723/72XXXXXX, prior to further flight, replace the CCU with a 
spare CCU from the operator's stock that has one of the following P/
N: 462650-21, 462650-22, or 462650-23. Following accomplishment of 
the replacement, the deactivation specified in paragraphs (a), (b), 
and (c) of this AD is no longer required, and the CCU's may be 
reactivated.
    (ii) If any connector has P/N M83723/71XXXXXX or P/N M83723/
72XXXXXX, prior to further flight, modify the rear cover (40) of the 
CCU assembly [including aligning the center hole of the insulator 
with the center hole on the rear cover (40), and ensuring that the 
top edge of the insulator is parallel to the top edge of the rear 
cover), and reidentify the CCU, in accordance with the service 
bulletin. Following accomplishment of the modification, the 
deactivation specified in paragraphs (a), (b), and (c) of this AD is 
no longer required, and the CCU's may be reactivated.

Spares

    (e) As of the effective date of this AD, no person shall install 
on any airplane any part (identified under ``Key Word''), having a 
``Spare Part No.'' listed in paragraph 2.D., ``Parts Necessary to 
Change Spares,'' of Boeing Alert Service Bulletin MD11-25A253, dated 
March 10, 2000.

Alternative Methods of Compliance

    (f) 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, Transport Airplane Directorate. 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

    (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 July 14, 2000.
John J. Hickey,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-18402 Filed 7-26-00; 8:45 am]
BILLING CODE 4910-13-U