AD 2000-24-17

[Federal Register Volume 65, Number 233 (Monday, December 4, 2000)]
[Rules and Regulations]
[Pages 75624-75627]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-30442]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-38-AD; Amendment 39-12024; AD 2000-24-17]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes 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). This amendment requires, 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 this amendment 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: Effective January 8, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 8, 2001.

ADDRESSES: 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: 
Technical Publications Business Administration, Dept. C1-L51 (2-60). 
This information may be examined at the Federal Aviation Administration 
(FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, 
SW., Renton, Washington; or at the FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood,

[[Page 75625]]

California; or at the Office of the Federal Register, 800 North Capitol 
Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: 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.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2000-08-03, 
amendment 39-11689 (65 FR 21134, April 20, 2000), which is applicable 
to certain McDonnell Douglas Model MD-11 series airplanes, was 
published in the Federal Register on July 27, 2000 (65 FR 46223). The 
action proposed to continue to require deactivation of the forward and 
center cargo control units (CCU). The action also proposed to 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.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

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 will be affected by this 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 required in this AD action will 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 required 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 required in this AD action, it will take approximately 1 work 
hour per airplane to accomplish, at an average labor rate of $60 per 
work hour. Required parts will be supplied by the manufacturer of the 
CCU at no cost to the operators. Based on these figures, the cost 
impact of the modification required 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 required in this AD action, it will take approximately 1 work 
hour per airplane to accomplish, at an average labor rate of $60 per 
work hour. Required parts will be supplied by the manufacturer of the 
CCU at no cost to the operators. Based on these figures, the cost 
impact of the replacement required 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 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.

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.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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 removing amendment 39-11689 (65 FR 
21134, April 20, 2000), and by adding a new airworthiness directive 
(AD), amendment 39-12024, to read as follows:

2000-24-17 McDonnell Douglas: Amendment 39-12024. 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.

[[Page 75626]]

Group 1 Airplanes

          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    \1\ 48775-48779
          48624              48756              48780             48532
 
\1\ Inclusive.

Group 2 Airplanes:

          48555              48556              48581              48630              48557              48539
          48558              48559              48616              48560              48617              48618
          48561              48629              48562              48563              48757              48540
          48564              48634              48541              48798    \1\ 48781-48792
          48794              48799              48801              48800    \1\ 48802-48806
 
\1\ 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
 

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

[[Page 75627]]

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. 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.

Incorporation by Reference

    (h) The actions required by paragraphs (d)(2), (d)(2)(i) and 
(d)(2)(ii) shall be done in accordance with Boeing Alert Service 
Bulletin MD11-25A253, dated March 10, 2000. 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: 
Technical Publications Business Administration, Dept. C1-L51 (2-60). 
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

    (i) This amendment becomes effective on January 8, 2001.

    Issued in Renton, Washington, on November 22, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-30442 Filed 12-1-00; 8:45 am]
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