[Federal Register Volume 71, Number 16 (Wednesday, January 25, 2006)]
[Proposed Rules]
[Pages 4062-4065]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-897]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23675; Directorate Identifier 2001-NM-320-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2-203 and A300 B4-
203 Airplanes; Model A300 B4-600, B4-600R, and F4-600R Series 
Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called 
A300-600 Series Airplanes); and Model A310-200 and -300 Series 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that affects certain Airbus Model A300 series airplanes 
and all Model A300-600 and A310 series airplanes. That AD currently 
requires repetitive inspections of the pitch trim system to detect 
continuity defects in the autotrim function, and follow-on corrective 
actions if necessary. For certain airplanes, this proposed AD would 
also require replacing the flight augmentation computers (FACs) with 
new improved FACs. This proposed AD also revises the applicability of 
the existing AD. This proposed AD results from the development of a 
final action intended to address the unsafe condition. We are proposing 
this AD to prevent a sudden change in pitch due to an out-of-trim 
condition combined with an autopilot disconnect, which could result in 
reduced controllability of the airplane.

DATES: We must receive comments on this proposed AD by February 24, 
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.
    For service information identified in this proposed AD, contact 
Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street, SW., room PL-
401, on the plaza level of the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2006-23675; 
Directorate Identifier 2001-NM-320-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 our 
docket web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual

[[Page 4063]]

who sent the comment (or signed the comment on behalf of an 
association, business, labor union, etc.). You can review the DOT's 
complete Privacy Act Statement in the Federal Register published on 
April 11, 2000 (65 FR 19477-78), or you may visit http://dms.dot.gov.

Examining the Docket

    You can 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 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 DMS receives them.

Discussion

    On November 6, 2000, we issued AD 2000-23-07, amendment 39-11977 
(65 FR 68876, November 15, 2000), for certain Airbus Model A300 series 
airplanes and all Model A300-600 and A310 series airplanes. That AD 
requires repetitive inspections of the pitch trim system to detect any 
continuity defect in the autotrim function, and follow-on corrective 
actions if necessary. That AD was prompted by issuance of mandatory 
continuing airworthiness information by the Direction Generale de 
l'Aviation Civile (DGAC), which is the airworthiness authority for 
France. We issued that AD to prevent a sudden change in pitch due to an 
out-of-trim condition combined with an autopilot disconnect, which 
could result in reduced controllability of the airplane.

Actions Since Existing AD Was Issued

    One operator reported an undetected slow pitch trim movement in the 
nose-down direction leading to an out-of-trim situation and airplane 
nose-down attitude during climb phase after autopilot engagement. 
Investigation revealed an open circuit in the existing flight 
augmentation computer (FAC) software design did not allow the FAC pitch 
trim monitoring function to provide automatic disengagement of pitch 
trim.
    Since AD 2000-23-07 was issued, as a result of these new findings 
and the incidents that prompted AD 2000-23-07, a new FAC was developed 
for Model A300-600 and A310-200 and -300 series airplanes to restore 
full capability of the FAC autotrim monitoring function.
    In AD 2000-23-07, we explain that we consider the requirements 
``interim action'' and were considering further rulemaking. We now have 
determined that further rulemaking is indeed necessary, and this 
proposed AD follows from that determination.

Relevant Service Information

    Airbus has issued Service Bulletins A300-22-6050, dated October 8, 
2004, and A310-22-2058, dated April 6, 2005. The service bulletins 
describe procedures for replacing the FACs with new improved FACs. To 
ensure the continued airworthiness of these airplanes in France, the 
DGAC mandated the service information by issuing French airworthiness 
directive F-2005-111 R1, dated December 21, 2005. (The DGAC also 
mandated Airbus Service Bulletin A300-22-6041, described in AD 2000-23-
07, for Model A300 B2-203 and A300 B4-203 airplanes, in French 
airworthiness directive F-2000-115-304 R5, dated July 6, 2005.) 
Accomplishing the actions specified in the service bulletins is 
intended to adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that AD action is 
necessary for airplanes of this type design that are certificated for 
operation in the United States.
    We are proposing to supersede AD 2000-23-07. This proposed AD would 
retain the requirements of the existing AD. This action would also 
require accomplishing the actions specified in the service information 
described in this proposed AD.

Explanation of Changes to Existing AD

    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.
    AD 2000-23-07 requires operators to report their inspection 
findings. We no longer need this information and have removed this 
requirement from this proposed AD.
    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.

Costs of Compliance

    This AD would affect about 86 airplanes of U.S. registry. The 
following table provides the estimated costs for U.S. operators to 
comply with this proposed AD.

                                                                     Cost Estimates
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                                                                                Hourly labor
               Action                    Service bulletins       Work hours         rate         Parts cost                Total per airplane
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Inspection required by AD 2000-03-    A300-22A6042, A300-                   1             $65            None  $65, per inspection cycle.
 07, per inspection cycle.             22A0115, A310-22A2053.
Proposed FAC replacement............  A300-22-6050, A310-22-                9             $65          $2,677  $3,262.
                                       2058.
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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

[[Page 4064]]

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 FAA amends Sec.  39.13 by removing amendment 39-11977 (65 FR 
68876, November 15, 2000) and adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2006-23675; Directorate Identifier 2001-NM-
320-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this AD action by February 24, 2006.

Affected ADs

    (b) This AD supersedes AD 2000-23-07.

Applicability

    (c) This AD applies to the following Airbus airplanes, 
certificated in any category.
    (1) Model A300 B2-203 and A300 B4-203 airplanes, as identified 
in Airbus Service Bulletin A300-22A0115, Revision 02, dated March 7, 
2000.
    (2) Model A300 B4-601, B4-603, B4-620, B4-622, A300 B4-605R, B4-
622R, A300 F4-605R, F4-622R, and A300 C4-605R Variant F airplanes, 
except those modified in production by Airbus Modification 12932.
    (3) Model A310-203, -204, -221, -222, -304, -322, -324, and -325 
airplanes, except those modified in production by Airbus 
Modification 12932.

Unsafe Condition

    (d) This AD results from the development of final action 
intended to address the unsafe condition. We are issuing this AD to 
prevent a sudden change in pitch due to an out-of-trim condition 
combined with an autopilot disconnect, which could result in reduced 
controllability of the airplane.

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 2000-23-07

Repetitive Inspections

    (f) For airplanes subject to the requirements of AD 2000-23-07: 
At the applicable time specified by paragraph (f)(1) or (f)(2) of 
this AD, perform an inspection of the autotrim function by testing 
the flight control computer (FCC)/flight augmentation computer (FAC) 
integrity in logic activation of the autotrim, in accordance with 
Airbus Service Bulletin A300-22A6042, Revision 01 (for Model A300-
600 series airplanes); A300-22A0115, Revision 02 (for Model A300 
series airplanes); or A310-22A2053, Revision 01 (for Model A310 
series airplanes); all dated March 7, 2000; as applicable. If any 
discrepancy is found, prior to further flight, perform all 
applicable corrective actions (including trouble-shooting; replacing 
the FCC and/or FAC, as applicable; retesting; checking the wires 
between certain FCC and FAC pins; and repairing damaged wires) in 
accordance with the applicable service bulletin. Repeat the 
inspection thereafter at intervals not to exceed 500 flight hours. 
Replacement of both FACs in accordance with paragraph (g) of this AD 
terminates the inspection requirements of this paragraph.
    (1) For airplanes on which the pitch trim system test has been 
performed in accordance with the requirements of AD 2000-02-04, 
amendment 39-11522: Inspect within 500 flight hours after 
accomplishment of the test required by that AD, or within 20 days 
after December 20, 2000 (the effective date of AD 2000-23-07, 
whichever occurs later.
    (2) For all other airplanes: Inspect within 20 days after 
December 20, 2000.

New Requirements of This AD

FAC Replacement

    (g) At the time specified in Table 1 of this AD, replace the two 
FACs with new FACs in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-22-6050, dated October 
8, 2004, or A310-22-2058, dated April 6, 2005; as applicable.

               Table 1.--Compliance Times To Replace FACs
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                                                    Required compliance
                                                      time after the
 Airplane  model/series       Configuration       effective date of this
                                                            AD
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A300-600...............  Without accomplishment   24 months.
                          of Airbus Service
                          Bulletin A300-22-6041,
                          Revision 01, dated
                          February 21, 2001, or
                          previous version, or
                          Modification 12277.
                         And without
                          accomplishment of
                          Airbus Service
                          Bulletin A300-22-6050,
                          dated October 8, 2004,
                          or Modification 12932.
                         With accomplishment of   36 months.
                          Airbus Service
                          Bulletin A300-22-6041,
                          Revision 01, dated
                          February 21, 2001, or
                          previous version, or
                          Modification 12277.
                         And without
                          accomplishment of
                          Airbus Service
                          Bulletin A300-22-6050,
                          dated October 8, 2004,
                          or Modification 12932.
A310...................  Without accomplishment   24 months.
                          of Airbus Service
                          Bulletin A310-22-2052,
                          Revision 01, dated
                          November 8, 2001, or
                          previous version, or
                          Modification 12277.
                         And without
                          accomplishment of
                          Airbus Service
                          Bulletin A310-22-2058,
                          dated April 6, 2005,
                          or Modification 12931.
                         With accomplishment of   36 months.
                          Airbus Service
                          Bulletin A310-22-2052,
                          Revision 01, dated
                          November 8, 2001, or
                          previous version, or
                          Modification 12277.

[[Page 4065]]

 
                         And without
                          accomplishment of
                          Airbus Service
                          Bulletin A310-22-2058,
                          dated April 6, 2005,
                          or Modification 12931.
------------------------------------------------------------------------

Part Installation

    (h) On or after the effective date of this AD, no person may 
install, on any airplane, any FAC having P/N B471AAM7 (for Model 
A300-600 series airplanes) or FAC P/N B471ABM4 (for Model A310 
series airplanes), unless the FAC is in compliance with this AD.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, 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 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (j) The subject of this AD is addressed in French airworthiness 
directives F-2005-111 R1, dated December 21, 2005, and F-2000-115-
304 R5, dated July 6, 2005.

    Issued in Renton, Washington, on January 17, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-897 Filed 1-24-06; 8:45 am]
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