[Federal Register Volume 71, Number 163 (Wednesday, August 23, 2006)]
[Proposed Rules]
[Pages 49385-49387]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-13964]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 71, No. 163 / Wednesday, August 23, 2006 / 
Proposed Rules  

[[Page 49385]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25670; Directorate Identifier 2006-NM-027-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Airbus Model A300 B2 and B4 series airplanes. This proposed 
AD would require revising the airplane flight manual (AFM) to include 
procedures for resetting the trim and pitch trim levers after each 
landing, determining which servomotor moves the pitch trim control 
wheel, and doing applicable other specified actions. This proposed AD 
also provides for optional terminating actions for those requirements. 
This proposed AD results from a report of a sudden nose-up movement 
after disengagement of the autopilot in cruise. We are proposing this 
AD to ensure that the flightcrew is aware of the procedures for 
resetting the trim and pitch trim levers after each landing and to 
prevent failure of the servomotors of the pitch trim systems during 
flight. Failure of the servomotors of the pitch trim systems could 
result in uncommanded nose-up movement of the control surface of the 
pitch trim systems after disengagement of the autopilot in cruise.

DATES: We must receive comments on this proposed AD by September 22, 
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 Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Thomas Stafford, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1622; fax (425) 227-1149.

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 ``FAA-2006-
25670; Directorate Identifier 2006-NM-027-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 you 
may 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

    The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France, notified us that an 
unsafe condition may exist on certain Airbus Model A300 B2 and B4 
series airplanes. The DGAC advises that a sudden nose-up movement after 
disengagement of the autopilot in cruise occurred on a Model A300 
airplane. At the time of the incident, the first pitch trim system 
(pitch trim 1) was inoperative before the flight and the second pitch 
trim system (pitch trim 2) had tripped. During the resulting 
investigation, the manufacturer identified a failure mode of the 
servomotors of the pitch trim systems as the cause of the incident. 
This condition, if not corrected, could result in uncommanded nose-up 
movement of the control surface of the pitch trim systems after 
disengagement of the autopilot in cruise.

Relevant Service Information

    Airbus has issued Temporary Revision (TR) 4.03.00/04, Issue 02, 
dated November 18, 2003, to the A300 Airplane Flight Manual (AFM). The 
TR describes a procedure for the flightcrew to follow after each 
landing of the airplane. The procedure involves resetting the trim and 
pitch trim. This procedure is to be inserted into the Normal Procedures 
section of the AFM.
    Airbus also has issued TR No. 22-001, dated April 11, 2003, of 
Chapter 22-23-00 of Airbus A300 Fault Isolation Manual. The TR 
describes procedures for determining which servomotor moves the pitch 
trim control wheel and doing applicable other specified actions. The 
applicable other specified actions involve replacing one or both

[[Page 49386]]

servomotors of the pitch trim systems with new servomotors or 
dispatching the airplane with both servomotors deactivated in 
accordance with the Master Minimum Equipment List (MMEL).
    In addition, Airbus issued Service Bulletin A300-22-0119, dated May 
13, 2005. The service bulletin describes optional procedures for 
replacing the pitch trim servomotors in the attachment area of the 
horizontal and vertical stabilizers with new servomotors. The service 
bulletin refers to Thales Service Bulletin V1AM-22-005, Revision 01, 
dated July 27, 2005, as an additional source of service information for 
doing the replacement.
    Further, Airbus issued Service Bulletin A300-22-0120, dated May 13, 
2005. The service bulletin describes procedures for repetitive 
preventative maintenance tasks of any pitch trim servomotor replaced in 
accordance with Service Bulletin A300-22-0119. The service bulletin 
refers to Thales Service Bulletin V1AM-22-006, Revision 01, dated July 
26, 2005, as an additional source of service information for doing the 
preventative maintenance task.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The DGAC mandated 
Airbus TR 4.03.00/04, Airbus TR No. 22-001, and Airbus Service Bulletin 
A300-22-0120 for any pitch trim servomotor replaced in accordance with 
Airbus Service Bulletin A300-22-0119. In addition, the DGAC mandated 
incorporation of Airbus TR No. 1.22/01Z, Revision 2, into the MMEL. The 
DGAC also issued French airworthiness directives F-2003-291 R1, dated 
July 6, 2005, and F-2005-109, dated July 6, 2005, to ensure the 
continued airworthiness of these airplanes in France.

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 we need to 
issue an AD for airplanes of this type design that are certificated for 
operation in the United States.
    Therefore, we are proposing this AD, which would require 
accomplishing the actions specified in Airbus TR 4.03.00/04, Airbus TR 
No. 22-001, and Airbus Service Bulletin A300-22-0120 for any pitch trim 
servomotor replaced in accordance with Airbus Service Bulletin A300-22-
0119, as described previously.

Clarification Between the Proposed AD and French Airworthiness 
Directive F-2003-291 R1

    Although the French airworthiness directive F-2003-291 R1 mandates 
incorporation of Airbus TR No. 1.22/01Z, Revision 2, into the MMEL, 
this proposed AD does not include that requirement. The procedures 
specified in Airbus TR No. 1.22/01Z have already been incorporated into 
the MMEL for the U.S. fleet.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD. The average labor rate per hour is 
$80.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                  Number of U.S.-
              Action                  Work hours             Parts            Cost per airplane     registered                  Fleet cost
                                                                                                     airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
AFM revision......................               1  None..................  $80.................              23  $1,840.
Determination if pitch trim                      1  None..................  $80.................              23  $1,840.
 control wheel moves.
Optional replacement..............               3  $264..................  $504................              23  $11,592.
Optional repetitive preventative                 3  None..................  $240, per task cycle              23  $5,520, per task cycle.
 maintenance tasks.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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:

[[Page 49387]]

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 
adding the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2006-25670; Directorate Identifier 2006-NM-
027-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by September 
22, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Airbus Model A300 airplanes; 
certificated in any category; except the following airplanes:
    (1) Model A300 B4-220, A300 B4-203, and A300 B2-203 airplanes in 
a forward facing crew cockpit certified configuration;
    (2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes;
    (3) Model A300 B4-605R and B4-622R airplanes;
    (4) Model A300 F4-605R and F4-622R airplanes; and
    (5) Airbus Model A300 C4-605R Variant F airplanes.

Unsafe Condition

    (d) This AD results from a report of a sudden nose-up movement 
after disengagement of the autopilot in cruise. We are issuing this 
AD to ensure that the flightcrew is aware of the procedures for 
resetting the trim and pitch trim levers after each landing and to 
prevent failure of the servomotors of the pitch trim systems during 
flight. Failure of the servomotors of the pitch trim systems could 
result in uncommanded nose up movement of the control surface of the 
pitch trim systems after disengagement of the autopilot in cruise.

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.

Revision of Airplane Flight Manual (AFM)

    (f) Within 14 days after the effective date of this AD, revise 
the Normal Procedures section of the Airbus A300 AFM to include the 
information in Airbus A300 Temporary Revision (TR) 4.03.00/04, Issue 
02, dated November 18, 2003, as specified in the TR.

    Note 1: This may be done by inserting a copy of TR 4.03.00/04, 
Issue 02, in the AFM. When the TR has been included in the general 
revisions of the AFM, the general revisions may be inserted in the 
AFM, provided the relevant information in the general revision is 
identical to that in the TR.

Determination if Pitch Trim Control Wheel Moves

    (g) Following accomplishment of the AFM revision required by 
paragraph (f) of this AD: After each landing and before shutting 
down the engines, do the AFM procedures specified in Airbus A300 TR 
4.03.00/04, Issue 02, dated November 18, 2003.

Determination if Servomotor Moves

    (h) Before further flight after any movement reported in 
accordance with paragraph (g) of this AD, determine which servomotor 
moves the pitch trim control wheel, and do applicable other 
specified actions in accordance with Airbus TR No. 22-001, dated 
April 11, 2003, of Chapter 22-23-00 of Airbus A300 Fault Isolation 
Manual.

    Note 2: Airbus TR No. 22-001 contains a typographical error. The 
TR incorrectly refers to ``MM 22-23-39'' as the appropriate source 
of service information for replacing the pitch trim actuator; the 
correct reference is ``MM 22-23-29.''

Optional Replacement of the Pitch Trim Servomotors

    (i) Replace the pitch trim servomotors in the attachment area of 
the horizontal and vertical stabilizers with new servomotors, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-22-0119, dated May 13, 2005.

    Note 3: Airbus Service Bulletin A300-22-0119, dated May 13, 
2005, refers to Thales Service Bulletin V1AM-22-005, Revision 01, 
dated July 27, 2005, as an additional source of service information 
for doing the replacement.

Repetitive Preventative Maintenance Tasks

    (j) Within 12,000 flight hours after replacing one or both 
servomotors in accordance with paragraph (h) or (i) of this AD, or 
within 6 months after the effective date of this AD, whichever 
occurs later, do the preventative maintenance task of the pitch trim 
servomotor(s), in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-22-0120, dated May 13, 2005. Repeat the 
preventative maintenance task thereafter at intervals not to exceed 
12,000 flight hours.

    Note 4: Airbus Service Bulletin A300-22-0120, dated May 13, 
2005, refers to Thales Service Bulletin V1AM-22-006, Revision 01, 
dated July 26, 2005, as an additional source of service information 
for doing the preventative maintenance task.

Removal of AFM Revision

    (k) After accomplishing the actions specified in paragraph (i) 
and the initial task in paragraph (j) of this AD, the AFM revision 
required by paragraph (f) of this AD may be removed, and the 
requirements of paragraphs (g) and (h) of this AD are no longer 
required.

No Reporting

    (l) Although Airbus Service Bulletin A300-22-0120 specifies to 
submit certain information to the manufacturer, this AD does not 
include that a requirement.

Alternative Methods of Compliance (AMOCs)

    (m)(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 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.

Related Information

    (n) French airworthiness directives F-2003-291 R1, issued July 
6, 2005, and F-2005-109, issued July 6, 2005, also addresses the 
subject of this AD.

    Issued in Renton, Washington, on August 15, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-13964 Filed 8-22-06; 8:45 am]
BILLING CODE 4910-13-P