[Federal Register Volume 71, Number 31 (Wednesday, February 15, 2006)]
[Proposed Rules]
[Pages 7880-7883]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-2176]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23850; Directorate Identifier 2005-NM-126-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-10-10F and 
MD-10-30F Airplanes and Model MD-11 and MD-11F Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain McDonnell Douglas Model MD-11 
series airplanes. The existing AD 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. The 
existing AD also requires an inspection to determine the serial number 
of the FMCs; and follow-on corrective actions, if necessary, which 
terminate the AFM revision. The existing AD also requires an inspection 
to verify if a certain modification is on the identification plates of 
the FMCs; and applicable follow-on and corrective actions. This 
proposed AD would require installation of upgraded flight management 
computer software, which would terminate the existing AD. This proposed 
AD would also add airplanes to the applicability, including adding 
Model MD-10-10F and MD-10-30F airplanes. This proposed AD results from 
a report that the FMC does not acknowledge the pre-set glareshield 
control panel (GCP) altitude when profile (PROF) mode is engaged in 
descent mode. We are proposing this AD to prevent the un-commanded 
descent of an airplane below the selected level-off altitude, which 
could result in an unacceptable reduction in the separation between the 
airplane and nearby air traffic or terrain.

DATES: We must receive comments on this proposed AD by April 3, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to
http://dms.dot.gov and follow the instructions for sending your 
comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Boeing Commercial Airplanes, Long Beach Division, 3855 
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and 
Service Management, Dept. C1-L5A (D800-0024), for service information 
identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Natalie Phan-Tran, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712-4137; telephone (562) 627-5343; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``Docket No. 
FAA-2006-23850; Directorate Identifier 2005-NM-126-AD'' at the 
beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of the 
proposed AD. We will consider all comments received by the closing date 
and may amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or visit 
http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    On October 15, 2001, we issued AD 2001-21-05, amendment 39-12476 
(66 FR 53335, October 22, 2001), for certain McDonnell Douglas Model 
MD-11 series airplanes. That AD 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

[[Page 7881]]

determine the serial number of the FMCs; and follow-on corrective 
actions, if necessary, which terminate the AFM revision. That AD also 
requires an inspection to verify if a certain modification is on the 
identification plates of the FMCs; and applicable follow-on and 
corrective actions. That AD resulted from a report indicating that, due 
to incorrect multiplexers that were installed in the FMC's during 
production, certain data busses failed simultaneously during a ground 
test. We issued that AD 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.

Actions Since Existing AD Was Issued

    Since we issued AD 2001-21-05, we have received a report that an 
operator has discovered an anomaly during a descent phase of flight 
where the FMC does not acknowledge the pre-set glareshield control 
panel (GCP) altitude when profile (PROF) mode is engaged in descent 
mode. As a result of the anomaly, the airplane may deviate below the 
selected level-off altitude. This condition, if not corrected, could 
result in an unacceptable reduction in the separation between the 
airplane and nearby air traffic or terrain.

Relevant Service Information

    We have reviewed Boeing Service Bulletin MD11-34-068, Revision 3, 
dated April 6, 2004 (for Model MD-11 and MD-11F airplanes). The service 
bulletin describes procedures for installing hardware and software to 
upgrade the flight management computer from P/N 4059050-912 to P/N 
4059050-920. The service bulletin refers to Honeywell Service Bulletin 
4059050-34-0010, dated March 19, 2003, as an additional source of 
service information for doing the actions.
    We have reviewed Boeing Service Bulletin MD11-34-129, dated 
September 22, 2004 (for Model MD-11 and MD-11F airplanes). The service 
bulletin describes procedures for installing new software in the main 
avionics rack and reidentifying FMC-1 and FMC-2 to P/N 4059050-921. The 
service bulletin refers to Honeywell Alert Service Bulletin 4059050-34-
A6023, dated September 22, 2004, as an additional source of service 
information for doing the actions.
    We have reviewed Boeing Service Bulletin MD11-34-130, dated March 
16, 2005 (for Model MD-11 and MD-11F airplanes). The service bulletin 
describes procedures for installing new software in the main avionics 
rack and reidentifying FMCs to P/N 4059050-913. The service bulletin 
refers to Honeywell Alert Service Bulletin 4059050-34-A6024, dated 
March 9, 2005, as an additional source of service information for doing 
the actions.
    We have reviewed Boeing Service Bulletin MD10-31-053, Revision 1, 
dated June 14, 2005 (for Model MD-10-10F and MD-10-30F airplanes). The 
service bulletin describes procedures for installing new software in 
the main avionics rack and reidentifying the versatile integrated 
avionics (VIA) digital computer as P/N 4081580-903. The service 
bulletin refers to Honeywell Alert Service Bulletin 4081580-31-A6002, 
dated January 14, 2005, as an additional source of service information 
for doing the actions.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

Other Relevant Rulemaking

    We have previously issued AD 2004-18-04, amendment 39-13782 (69 FR 
53794, September 3, 2004) (A correction of the rule was published in 
the Federal Register on September 21, 2004 (69 FR 56480). That AD 
applies to all McDonnell Douglas MD-10-10F, MD-10-30F, MD-11, MD-11F, 
and 717-200 airplanes, and requires revising the Limitations section of 
the AFM to prohibit the use of the flight management system PROF mode 
for descent and/or approach operations unless certain conditions are 
met. Doing the applicable software/hardware upgrades that would be 
required by paragraphs (j) and (k) of this proposed AD are approved as 
an alternative method of compliance for the actions required by AD 
2004-18-04.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to develop on other airplanes of the 
same type design. For this reason, we are proposing this AD, which 
would supersede AD 2001-21-05. This proposed AD would retain the 
requirements of AD 2001-21-05 and would require accomplishing the 
actions specified in the service information described previously, 
which would terminate the requirements of the existing AD. This 
proposed AD also expands the applicability to include all Model MD-11 
and MD-11F airplanes and certain Model MD-10-10F and MD-10-30F 
airplanes.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

Explanation of Change to Applicability

    We have revised the applicability of the existing AD to identify 
model designations as published in the most recent type certificate 
data sheet for the affected models.

Clarification of Alternative Method of Compliance (AMOC) Paragraph

    We have revised this action to clarify the appropriate procedure 
for notifying the principal inspector before using any approved AMOC on 
any airplane to which the AMOC applies.

Change to Existing AD

    This proposed AD would retain all requirements of AD 2001-21-05. 
Since AD 2001-21-05 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
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                                             Corresponding  requirement
       Requirement in AD 2001-21-05             in this  proposed AD
------------------------------------------------------------------------
Paragraph (a).............................  Paragraph (f).
Paragraph (b).............................  Paragraph (g).
Paragraph (c).............................  Paragraph (h).
Paragraph (d).............................  Paragraph (i).
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Clarification of Paragraph Reference

    Paragraph (d) of AD 2001-21-05 references ``the inspection required 
by paragraph (a) of this AD.'' However, there is no inspection in 
paragraph (a) of AD 2001-21-05; the inspection is specified in 
paragraph (b) of AD 2001-21-05. We have the revised paragraph (i) of 
this proposed AD (specified as paragraph (d) of AD 2001-25-05) to 
reference ``the inspection required by paragraph (g) of this AD'' 
(specified as paragraph (b) of AD 2001-25-05).

Costs of Compliance

    There are about 230 airplanes of the affected design in the 
worldwide fleet and about 117 U.S.-registered airplanes. The following 
table provides the estimated costs for U.S. operators to comply with 
this proposed AD. The average labor rate per hour is $65.

[[Page 7882]]



                                                 Estimated Costs
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                                                                                         Number of
                                                                             Cost per      U.S.-
                     Action                       Work hours     Parts       airplane    registered   Fleet cost
                                                                                         airplanes
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AFM Revision, Inspections and Software                     2           $0         $130           59       $7,670
 Installation (required by AD 2001-21-05)......
Upgrade Software/Hardware (new proposed action)            2            0          130          117       15,210
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Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD 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.
    For the reasons discussed above, I certify that the 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. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-12476 (66 FR 53335, October 22, 2001) and adding 
the following new airworthiness directive (AD):

McDonnell Douglas: Docket No. FAA-2006-23850; Directorate Identifier 
2005-NM-126-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by April 3, 
2006.

Affected ADs

    (b) This AD supersedes AD 2001-21-05.

Applicability

    (c) This AD applies to McDonnell Douglas airplanes, as specified 
in paragraphs (c)(1) and (c)(2) of this AD, certificated in any 
category.
    (1) Model MD-10-10F and MD-10-30F airplanes, as identified in 
Boeing Service Bulletin MD10-31-053, Revision 1, dated June 14, 
2005.
    (2) All Model MD-11 and MD-11F airplanes.

Unsafe Condition

    (d) This AD results from a report that the flight management 
computer (FMC) does not acknowledge the pre-set glareshield control 
panel (GCP) altitude when profile (PROF) mode is engaged in descent 
mode. We are issuing this AD to prevent the un-commanded descent of 
an airplane below the selected level-off altitude, which could 
result in an unacceptable reduction in the separation between the 
airplane and nearby air traffic or terrain.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Requirements of AD 2001-21-05

Airplane Flight Manual (AFM) Revision

    (f) For MD-11 and MD-11F airplanes having manufacturer's 
fuselage numbers 0447 through 0552 inclusive, and 0554 through 0621 
inclusive: 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.''

Inspection

    (g) For MD-11 and MD-11F airplanes having manufacturer's 
fuselage numbers 0447 through 0552 inclusive, and 0554 through 0621 
inclusive: Within 90 days after November 26, 2001 (the effective 
date of AD 2001-21-05), do an inspection to verify that modification 
``AS'' is on the front and rear identification plates of 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 (f) of this AD may be removed 
from the AFM.

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

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


    Note 1: 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

[[Page 7883]]

installation and reidentification requirements of paragraphs (h)(2) 
and (i)(2) of this AD.

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

    (i) If modification ``AS'' is NOT found installed during the 
inspection required by paragraph (g) of this AD, before further 
flight, do the actions specified in paragraphs (i)(1), (i)(2), and 
(i)(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.

New Requirements of This AD

Upgrade Software/Hardware--Model MD-11 and MD-11F Airplanes

    (j) For Model MD-11 and MD-11F airplanes: Within 18 months after 
the effective date of this AD, upgrade the FMC software, and 
hardware as applicable, by doing the applicable actions specified in 
paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this AD. Doing this 
upgrade terminates the requirements of paragraphs (f) through (i) of 
this AD.
    (1) For airplanes on which FMC P/N 4059050-906 through -912 is 
installed: Install new software in the main avionics rack, and 
reidentify FMC-1 and FMC-2 as P/N 4059050-913, in accordance with 
the Accomplishment Instructions of Boeing Service Bulletin MD11-34-
130, dated March 16, 2005.


    Note 2: Boeing Service Bulletin MD11-34-130 refers to Honeywell 
Alert Service Bulletin 4059050-34-A6024, dated March 9, 2005, as an 
additional source of service information for doing the actions 
specified in paragraph (j)(1) of this AD.
    (2) For airplanes on which FMC P/N 4059050-920 is installed: 
Install new software in the main avionics rack, and reidentify FMC-1 
and FMC-2 as P/N 4059050-921, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin MD11-34-129, dated September 
22, 2004.


    Note 3: Boeing Service Bulletin MD11-34-129 refers to Honeywell 
Alert Service Bulletin 4059050-34-A6023, dated September 22, 2004, 
as an additional source of service information for doing the actions 
specified in paragraph (j)(2) of this AD.
    (3) For airplanes on which FMC P/N 4059050-906 through -911 is 
installed: In lieu of doing the software upgrade specified in 
paragraph (j)(1) of this AD, install new hardware and software and 
reidentify FMC-1 and FMC-2 as P/N 4059050-921, by doing all the 
applicable actions specified in the Accomplishment Instructions of 
McDonnell Douglas Service Bulletin MD11-34-085, Revision 01, dated 
September 20, 1999; Boeing Service Bulletin MD11-34-068, Revision 3, 
dated April 6, 2004; and Boeing Service Bulletin MD11-34-129, dated 
September 22, 2004.


    Note 4: McDonnell Douglas Service Bulletin MD11-34-085 
references Honeywell Service Bulletin 4059050-34-6020, Revision 1, 
dated April 30, 1999; Boeing Service Bulletin MD11-34-068 references 
Honeywell Service Bulletin 4059050-34-0010, dated March 19, 2003; 
and Boeing Service Bulletin MD11-34-129 refers to Honeywell Alert 
Service Bulletin 4059050-34-A6023, dated September 22, 2004; as 
additional sources of service information for the doing the actions 
specified in paragraph (j)(3) of this AD.
    (4) For airplanes on which FMC P/N 4059050-912 is installed: In 
lieu of doing the software upgrade specified in paragraph (j)(1) of 
this AD, install new hardware and software and reidentify FMC-1 and 
FMC-2 as P/N 4059050-921, by doing all the applicable actions 
specified in the Accomplishment Instructions of Boeing Service 
Bulletin MD11-34-068, Revision 3, dated April 6, 2004; and Boeing 
Service Bulletin MD11-34-129, dated September 22, 2004.


    Note 5: Boeing Service Bulletin MD11-34-068 references Honeywell 
Service Bulletin 4059050-34-0010, dated March 19, 2003; and Boeing 
Service Bulletin MD11-34-129 refers to Honeywell Alert Service 
Bulletin 4059050-34-A6023, dated September 22, 2004; as additional 
sources of service information for the doing the actions specified 
in paragraph (j)(4) of this AD.

Upgrade Software--Model MD-10-10F and MD-10-30F Airplanes

    (k) For Model MD-10-10F and MD-10-30F airplanes: Within 18 
months after the effective date of this AD, install new software in 
the main avionics rack and reidentify the versatile integrated 
avionics (VIA) digital computer as P/N 4081580-903, in accordance 
with the Accomplishment Instructions of Boeing Service Bulletin 
MD10-31-053, Revision 1, dated June 14, 2005.

    Note 6: Boeing Service Bulletin MD10-31-053 refers to Honeywell 
Alert Service Bulletin 4081580-31-A6002, dated January 14, 2005, as 
an additional source of service information for doing the actions 
specified in paragraph (k) of this AD.

Parts Installation

    (l) For Model MD-11 and MD-11F airplanes: As of the effective 
date of this AD, no person may install an FMC, P/N 4059050-906 
through -912, or -920, on any airplane; except as required by the 
actions specified in paragraphs (h), (i), and (j) of this AD.
    (m) For MD-10-10F and MD-10-30F airplanes: As of the effective 
date of this AD, no person may install a VIA digital computer, P/N 
4081580-901 or 4081580-902, on any airplane.

Alternative Methods of Compliance (AMOCs)

    (n)(1) The Manager, Los Angeles Aircraft Certification Office, 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.
    (3) AMOCs approved previously in accordance with AD 2001-21-05 
are approved as AMOCs for the corresponding provisions of paragraphs 
(f) through (i) of this AD.
    (4) Doing the actions required by paragraph (j) or (k) of this 
AD, as applicable, is approved as an AMOC for the actions required 
by AD 2004-18-04, amendment 39-13782.

    Issued in Renton, Washington, on February 1, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-2176 Filed 2-14-06; 8:45 am]
BILLING CODE 4910-13-P