AD 2001-21-05

[Federal Register Volume 66, Number 204 (Monday, October 22, 2001)]
[Rules and Regulations]
[Pages 53335-53337]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-26472]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-337-AD; Amendment 39-12476; AD 2001-21-05]
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 a revision of the Airplane Flight 
Manual (AFM) to alert the flightcrew that both flight management 
computers (FMC) must be installed and operational. That AD also 
requires an inspection to determine the serial number of the FMC's; and 
follow-on corrective actions, if necessary, which terminate the AFM 
revision. This amendment requires an inspection to verify if a certain 
modification is on the front and rear identification plates of the 
FMC's; and applicable follow-on and corrective actions. This amendment 
is prompted by the FAA's determination that further rulemaking action 
is necessary to ensure that all affected airplanes are inspected for 
suspected defective multiplexers. The actions specified by this AD are 
intended to prevent loss of airspeed and altitude indications on both 
primary flight displays in the cockpit, and/or loss or degradation of 
the autopilot functionality, and consequent failure of the data busses.

DATES: Effective November 26, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 26, 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: Data 
and Service Management, Dept. C1-L5A (D800-0024). This information may 
be examined at the Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, 
Washington; or at 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: Brett Portwood, Aerospace Engineer, 
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 98-15-14, 
amendment 39-10665 (63 FR 38464, July 17, 1998), which is applicable to 
certain McDonnell Douglas Model MD-11 series airplanes, was published 
in the Federal Register on April 19, 2001 (66 FR 20116). The action 
proposed to continue to require a revision of the Airplane Flight 
Manual to alert the flightcrew that both flight management computers 
(FMCs) must be installed and operational. This action also proposed to 
require an inspection to determine whether McDonnell Douglas 
Modification ``AS'' had been incorporated and applicable follow-on and 
corrective actions.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Commenter Concurs

    One operator indicates that it has no objections to the proposed 
actions, which it has already completed.

Request To Allow Verification of Prior Re-identification

    One operator states that ``if the Mod AS accomplishes the 
corrective action of the data bus failure condition, and was 
satisfactorily demonstrated and approved by the FAA, then the 
terminating action should be to `verify that the FMCs installed have 
Mod AS incorporated and are software updated to the -912 P/N.' There 
should be no need to confirm that a data bus failure condition does not 
exist.''
    The same commenter states that it has already accomplished the 
proposed terminating action by modifying all of its FMCs with Mod 
``AS'', and has accomplished the Honeywell and the McDonnell Douglas/
Boeing service bulletins to ensure that the software was updated to the 
-912 P/N. The FAA concurs that if the requirements of the applicable 
service bulletin have already been accomplished, this AD does not 
require that those actions be repeated. As a result, no change to the 
AD is necessary in this regard.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Cost Impact

    There are approximately 174 Model MD-11 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 59 
airplanes of U.S. registry will be affected by this AD.
    The actions that are currently required by AD 98-15-14 and retained 
in this AD 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 $3,540, or $60 per airplane.
    The new actions that are required by this AD 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 new requirements of this AD on U.S. operators is 
estimated to be $3,540 or $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

[[Page 53336]]

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 39-10665 (63 FR 
38464, July 17, 1998), and by adding a new airworthiness directive 
(AD), amendment 39-12476, to read as follows:

2001-21-05  McDonnell Douglas: Amendment 39-12476. Docket 2000-NM-
337-AD. Supersedes AD 98-15-14, Amendment 39-10665.

    Applicability: Model MD-11 series airplanes having 
manufacturer's fuselage numbers 0447 through 0552 inclusive, and 
0554 through 0621 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 (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 prevent loss of airspeed and altitude indications on both 
primary flight displays in the cockpit, and/or loss or degradation 
of the autopilot functionality, and consequent failure of the data 
busses, accomplish the following:

Restatement of Requirements of AD 98-15-14

Airplane Flight Manual (AFM) Revision

    (a) Within 5 days after May 20, 1998 (the effective date of AD 
98-10-01, amendment 39-10512), revise Section 1, page 5-1, of the 
Limitations Section of the FAA-approved AFM to include the following 
statement. This may be accomplished by inserting a copy of this AD 
into the AFM.

``Prior to dispatch of the airplane, both Flight Management Computer 
1 (FMC-1) and FMC-2 must be installed and operational.''

New Actions Required by This AD

Inspection

    (b) Within 90 days after the effective date of this AD, do an 
inspection to verify that modification ``AS'' is on the front and 
rear identification plates of flight management computer 1 (FMC-1) 
and FMC-2, per McDonnell Douglas Service Bulletin MD11-34-085, 
Revision 01, dated September 20, 1999. After the inspection has been 
done, the AFM revision required by paragraph (a) of this AD may be 
removed from the AFM.

Condition 1 (Modification ``AS'' Is Installed)

    (c) If modification ``AS'' is found installed during the 
inspection required by paragraph (b) of this AD, before further 
flight, do the actions specified in paragraphs (c)(1) and (c)(2) of 
this AD, per McDonnell Douglas Service Bulletin MD11-34-085, 
Revision 01, dated September 20, 1999.
    (1) Do a test of the FMC's in the flight compartment to ensure 
that modification ``AS'' is operational, and do applicable 
corrective actions, if necessary. Both FMC's must have modification 
``AS'' installed and pass the test before loading new software per 
paragraph (c)(2) of this AD.
    (2) Install new software and reidentify FMC-1 and FMC-2 as part 
number (P/N) 4059050-912.

    Note 2: McDonnell Douglas Service Bulletin MD11-34-085, Revision 
01, dated September 20, 1999, references Honeywell Service Bulletin 
4059050-34-6020, Revision 1, dated April 30, 1999, as an additional 
source of service information for the installation and 
reidentification requirements of paragraphs (c)(2) and (d)(2) of 
this AD.

Condition 2 (Modification ``AS'' Is Not Installed)

    (d) If modification ``AS'' is NOT found installed during the 
inspection required by paragraph (a) of this AD, before further 
flight, do the actions specified in paragraphs (d)(1), (d)(2), and 
(d)(3) of this AD, per McDonnell Douglas Service Bulletin MD11-34-
085, Revision 01, dated September 20, 1999.
    (1) Remove FMC-1 and FMC-2.
    (2) Install modification ``AS'' and new software, and reidentify 
FMC-1 and FMC-2 as P/N 4059050-912.
    (3) Install modified and reidentified FMC-1 and FMC-2.

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 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

    (f) 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

    (g) Except as required by paragraph (a) of this AD, the actions 
shall be done in accordance with McDonnell Douglas Service Bulletin 
MD11-34-085, Revision 01, dated September 20, 1999. 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 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 November 26, 2001.


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    Issued in Renton, Washington on October 15, 2001.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 01-26472 Filed 10-19-01; 8:45 am]
BILLING CODE 4910-13-U