Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes Equipped With General Electric CF6-50 Engines, 58318-58320 [E6-16201]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 71, Number 191 (Tuesday, October 3, 2006)]
[Proposed Rules]
[Pages 58318-58320]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-16201]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25965; Directorate Identifier 2006-NM-127-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes Equipped With General Electric CF6-50 Engines

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 Airbus Model A300 B2 and B4 series 
airplanes equipped with General Electric CF6-50 engines. The existing 
AD currently requires deactivating both thrust reversers and revising 
the airplane flight manual (AFM) to require performance penalties 
during certain takeoff conditions to ensure that safe and appropriate 
performance is achieved for airplanes on which both thrust reversers 
have been deactivated. This proposed AD would require one-time 
inspections of the directional pilot valve (DPV), the rocker arm and 
associated hardware, and corrective actions if necessary; reactivation 
of both thrust reversers; and repetitive inspections of the DPV and the 
associated control mechanism of the thrust reversers for incorrect 
assembly or excessive wear, and corrective actions if necessary. 
Accomplishing all of the proposed actions would allow the removal of 
the AFM limitations in the existing AD. This proposed AD results from 
reports indicating that the DPV was assembled incorrectly; further 
investigation revealed excessive wear on certain correctly assembled 
DPVs and the associated control mechanism. We are proposing this AD to 
prevent uncommanded in-flight deployment of a thrust reverser, which 
could result in reduced controllability of the airplane.

DATES: We must receive comments on this proposed AD by November 2, 
2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to  https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
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: Tom Stafford, Aerospace Engineer 
International Branch, ANM-116, FAA, International Branch, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; 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 ``Docket No. 
FAA-2006-25965; Directorate Identifier 2006-NM-127-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 https://
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 https://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at https://
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 April 19, 2002, we issued AD 2002-08-51, amendment 39-12728 (67 
FR 21569, May 1, 2002), for Airbus Model A300 B2 and B4 series 
airplanes equipped with General Electric CF6-50 engines. That AD 
requires deactivating both thrust reversers and revising the airplane 
flight manual (AFM) to require performance penalties during certain 
takeoff conditions to ensure that safe and appropriate performance is 
achieved for airplanes on which both thrust reversers have been 
deactivated. That AD resulted from the issuance of mandatory continuing 
airworthiness information by a foreign civil airworthiness authority. 
We issued that AD to prevent uncommanded in-flight deployment of a 
thrust reverser, which could result in reduced controllability of the 
airplane.

Actions Since Existing AD Was Issued

    The actions required by AD 2002-08-51 are considered ``interim 
action'' until final action was identified. We have determined that 
further rulemaking action to address that final action is necessary; 
this proposed AD follows from that determination. Since AD 2002-08-51 
was issued, Airbus issued service information that provides 
instructions for reactivating the thrust reversers through the 
implementation of a program that involves one-time and follow-on 
repetitive inspections, and parts replacement if necessary. We approved 
this program as an alternative method of compliance (AMOC) with the 
requirements of AD 2002-08-51, allowing for reactivation of the thrust 
reversers and removal of the AFM limitations.

Relevant Service Information

    Airbus has issued All Operators Telex (AOT) A300-78A0024, dated May 
29, 2002. The AOT describes using the procedures in the Airbus A300 
Airplane Maintenance Manual to reactivate the

[[Page 58319]]

thrust reversers after accomplishing an inspection for correct assembly 
or excessive wear of the directional pilot valve (DPV) and excessive 
wear of the DPV rocker arm, and corrective actions (parts replacement) 
if necessary. Accomplishing these actions would eliminate the need for 
the AFM limitations.
    Airbus has also issued Service Bulletin A300-78-0025, Revision 01, 
including Appendix 01, dated February 16, 2005. The service bulletin 
describes procedures for repetitive detailed visual inspections of the 
DPV and the associated control mechanism of the thrust reverser for 
incorrect assembly or excessive wear, and corrective actions if 
necessary. The inspections are done following reactivation of the 
thrust reversers. The corrective actions include repair of any 
discrepancies in the DPV and replacing any damaged parts in the 
associated control mechanism.
    The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France, mandated the Airbus 
service information and issued French airworthiness directives 2002-
293(B), dated June 12, 2002; and F-2005-208, dated December 21, 2005, 
to ensure the continued airworthiness of these airplanes in France.
    The Airbus AOT refers to Middle River Aircraft Systems CF6-50 Alert 
Service Bulletin 78A3040, Revision 2, dated June 18, 2004, (including 
Honeywell Service Bulletin 121332-78-1620, Revision 2, dated June 18, 
2004), as an additional source of service information for accomplishing 
the inspections. The Airbus service bulletin refers to Middle River 
Aircraft Component Maintenance Manual 78-31-06, Revision 10, dated May 
31, 2005, as an additional source of service information for replacing 
defective components.

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.
    This proposed AD would supersede AD 2002-08-51 and would retain the 
requirements of the existing AD. This proposed AD would also require 
inspections of the DPV and the rocker arm and associated hardware; 
reactivation of both thrust reversers; and repetitive inspections of 
the DPV and the associated control mechanism of the thrust reversers 
for incorrect assembly or excessive wear, and corrective actions if 
necessary. Accomplishing the inspections of the DPV and the rocker arm 
and associated hardware, followed by the reactivation of the thrust 
reversers, would eliminate the need for the AFM limitations required by 
the existing AD.

Clarification of Inspection Terminology

    In this proposed AD, the ``detailed visual inspection'' specified 
in the Airbus service bulletin, and the ``inspection'' required by the 
French airworthiness directives, are referred to as a ``detailed 
inspection.'' We have included the definition for a detailed inspection 
in a note in the proposed AD.

Change to Existing AD

    This proposed AD would retain all requirements of AD 2002-08-51. 
Since AD 2002-08-51 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
------------------------------------------------------------------------
                                           Corresponding requirement in
      Requirement in  AD 2002-08-51              this proposed AD
------------------------------------------------------------------------
Paragraph (a)...........................  Paragraph (f).
------------------------------------------------------------------------

Costs of Compliance

    This proposed AD would affect about 30 airplanes of U.S. registry.
    The actions that are required by AD 2002-08-51, and retained in 
this proposed AD take about 3 work hours per airplane, at an average 
labor rate of $80 per work hour. Based on these figures, the estimated 
cost of the currently required actions is $240 per airplane.
    The new proposed inspection and reactivation specified in Airbus 
AOT A300-78A0024 would take about 9 work hours per airplane, at an 
average labor rate of $80 per work hour. Based on these figures, the 
estimated cost of the new inspection and reactivation specified in this 
proposed AD for U.S. operators is $21,600, or $720 per airplane.
    The new proposed inspections specified in Airbus Service Bulletin 
A300-78-0025 would take about 7 work hours per airplane, at an average 
labor rate of $80 per work hour. Based on these figures, the estimated 
cost of the new inspections specified in this proposed AD for U.S. 
operators is $16,800, or $560 per airplane, per inspection cycle.

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.

[[Page 58320]]

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 39-12728 (67 FR 21569, May 1, 2002) and adding the 
following new airworthiness directive (AD):

Airbus: Docket No. FAA-2006-25965; Directorate Identifier 2006-NM-
127-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by November 
2, 2006.

Affected ADs

    (b) This AD supersedes AD 2002-08-51.

Applicability

    (c) This AD applies to Airbus Model A300 airplanes, certificated 
in any category, equipped with General Electric CF6-50 engines.

Unsafe Condition

    (d) This AD results from reports indicating that the directional 
pilot valve (DPV) was assembled incorrectly; further investigation 
revealed excessive wear on certain correctly assembled DPVs and the 
associated control mechanism. We are issuing this AD to prevent 
uncommanded in-flight deployment of a thrust reverser, 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 2002-08-51

Thrust Reverser Deactivation and Airplane Flight Manual (AFM) 
Revision

    (f) Within 72 clock hours after May 6, 2002 (the effective date 
of AD 2002-08-51), accomplish paragraphs (f)(1) and (f)(2) of this 
AD.
    (1) Deactivate both thrust reversers according to Airbus All 
Operators Telex A300/78A0023, dated April 5, 2002.
    (2) Revise the Limitations Section of the AFM to include the 
following (this may be accomplished by inserting a copy of this AD 
into the AFM):

    ``When the runway is wet or contaminated, reduce by five percent 
the corrected acceleration-stop distance resulting from the airplane 
flight manual takeoff performance analysis.

(Note: This supersedes any relief provided by the Master Minimum 
Equipment List (MMEL).)''

New Requirements of This AD

Inspections and Corrective Actions

    (g) Within 6 months after the effective date of this AD: Do the 
actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of this 
AD in consecutive order, in accordance with the procedures specified 
in Airbus All Operators Telex (AOT) A300-78A0024, dated May 29, 
2002, which ends the requirements in paragraph (f) of this AD.
    (1) Do a detailed inspection of the DPV on each thrust reverser 
for incorrect assembly, incorrect diameter, or excessive wear, by 
doing all the applicable actions, including all applicable 
corrective actions. All applicable corrective actions must be done 
before further flight.
    (2) Do a detailed inspection of the rocker arm of the DPV for 
excessive wear by doing all the applicable actions, including all 
applicable corrective actions. All applicable corrective actions 
must be done before further flight.
    (3) Reactivate both thrust reversers and do a one-time 
operational test before further flight.

    Note 1: Airbus AOT A300-78A0024, dated May 29, 2002, refers to 
Middle River Aircraft Systems CF6-50 Alert Service Bulletin 78A3040, 
Revision 2, dated June 18, 2004 (including Honeywell Service 
Bulletin 121332-78-1620, Revision 2, dated June 18, 2004), as an 
additional source of service information for accomplishing the 
inspections.


    Note 2: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

Repetitive Inspections/Corrective Actions

    (h) Within 18 months after accomplishing paragraph (g) of this 
AD: Do a detailed inspection of the DPV and the associated control 
mechanism of the thrust reverser for incorrect assembly or excessive 
wear, by doing all the applicable actions, including all applicable 
corrective actions, in accordance with Airbus Service Bulletin A300-
78-0025, Revision 01, excluding Appendix 01, dated February 16, 
2005. All applicable corrective actions must be done before further 
flight. Repeat the inspection thereafter at intervals not to exceed 
8,000 flight hours.

    Note 3: Airbus Service Bulletin A300-78-0025, Revision 01, dated 
February 16, 2005, refers to Middle River Aircraft Systems Component 
Maintenance Manual 78-31-06, Revision 10, dated May 31, 2005, as an 
additional source of service information for replacing defective 
components.

Actions Accomplished Previously

    (i) Inspections and corrective actions done before the effective 
date of this AD in accordance with Airbus Service Bulletin A300-78-
0025, dated July 21, 2004, is acceptable for compliance with the 
corresponding requirements of paragraph (h) of this AD.

Alternative Methods of Compliance (AMOCs)

    (j)(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) AMOCs approved previously in accordance with AD 2002-08-51, 
are not approved as AMOCs with this AD.
    (3) 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

    (k) French airworthiness directives 2002-293(B), dated June 12, 
2002, and F-2005-208, dated December 21, 2005, also address the 
subject of this AD.

    Issued in Renton, Washington, on September 22, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-16201 Filed 10-2-06; 8:45 am]
BILLING CODE 4910-13-P