Airworthiness Directive · Amendment 39-14715 · McDonnell Douglas Model MD-10-10F and MD-10-30F Airplanes and Model MD-11 and MD-11F Airplanes
McDonnell Douglas Model MD-10-10F and MD-10-30F Airplanes and Model MD-11 and MD-11F Airplanes
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.
The FAA is superseding an existing airworthiness directive (AD), which applies to certain McDonnell Douglas Model MD-11 series airplanes. That AD currently requires a revision of the airplane flight manual (AFM) to alert the flightcrew that both flight management computers (FMCs) must be installed and operational. That 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. 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. This new AD requires installation of upgraded FMC software, which would terminate the existing AD. This new AD also adds airplanes to the applicability, including adding Model MD-10-10F and MD-10-30F airplanes. This 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 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.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
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.”
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.
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 installation and reidentification requirements of paragraphs (h)(2) and (i)(2) of this AD.
(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.
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, 2005; 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 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, 2005; 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 doing the actions specified in paragraph (j)(4) of this AD.
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.
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.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
