[Federal Register Volume 67, Number 84 (Wednesday, May 1, 2002)]
[Rules and Regulations]
[Pages 21569-21572]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-10245]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-107-AD; Amendment 39-12728; AD 2002-08-51]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting airworthiness directive (AD) 2002-08-51 that was sent 
previously to all known U.S. owners and operators of Airbus Model A300 
B2 and B4 series airplanes equipped with General Electric CF6-50 
engines by individual notices. This 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. This action is 
prompted by issuance of mandatory continuing airworthiness information 
by a foreign civil airworthiness authority. The actions specified by 
this AD are intended to prevent uncommanded in-flight deployment of a 
thrust reverser, which could result in reduced controllability of the 
airplane.

DATES: Effective May 6, 2002, to all persons except those persons to 
whom it was made immediately effective by emergency AD 2002-08-51, 
issued April 8, 2002, which contained the requirements of this 
amendment.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 6, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before May 31, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-107-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal

[[Page 21570]]

holidays. Comments may be submitted via fax to (425) 227-1232. Comments 
may also be sent via the Internet using the following address: [email protected]. Comments sent via fax or the Internet must contain 
``Docket No. 2002-NM-107-AD'' in the subject line and need not be 
submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The applicable service information may be obtained from Airbus 
Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. 
This information may be examined at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, 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: On April 8, 2002, the FAA issued emergency 
AD 2002-08-51, which is applicable to Airbus Model A300 B2 and B4 
series airplanes equipped with General Electric CF6-50 engines.
    The FAA has received a report that, on February 16, 2002, 
uncommanded deployment of a thrust reverser occurred on the number 1 
engine of a McDonnell Douglas Model DC-10-30 airplane equipped with 
General Electric CF6-50 engines. The uncommanded deployment occurred 
following climb and level-out at 17,000 feet. The flightcrew reported 
severe buffeting of the airplane with yaw to the left and pitch down of 
about five degrees. The ``REV UNLOCK'' light was illuminated prior to 
onset of the buffeting. The flightcrew shut down the engine, dumped 
fuel, turned back to the departure airport, and landed the airplane. No 
injuries were reported among passengers or crew.
    Uncommanded deployment of a thrust reverser with a dual translating 
cowl requires a minimum of two failures: (1) The over pressure shut-off 
valve (OPSOV) must let pressure enter into the thrust reverser 
actuation system; and (2) the directional pilot valve (DPV) must 
command this pressure in the deploy direction. The cause of the 
presence of pressure in the thrust reverser system has not been 
determined.
    Results of a subsequent investigation by the engine manufacturer 
revealed that the DPV was misassembled during overhaul by the DPV 
manufacturer in 1997. The DPV was installed on the incident airplane in 
1999. The misassembly involved incorrect installation of a washer and 
bushing in the DPV piston/poppet assembly. Results of vibration-table 
testing showed that a DPV misassembled in this way could change 
positions from ``stow command'' to ``deploy command'' on its own. When 
a DPV is in the ``deploy command'' position, a single failure of the 
OPSOV could result in an uncommanded deployment of the thrust reverser 
during flight. This condition, if not corrected, could result in 
reduced controllability of the airplane.
    Model A300 B2 and B4 series airplanes equipped with General 
Electric CF6-50 engines have the same nacelle and thrust reverser 
system as the airplane on which the event described previously 
occurred. Since a misassembled DPV may be installed on Model A300 B2 
and B4 series airplanes, those airplanes may be subject to the unsafe 
condition identified in this AD.

Explanation of Relevant Service Information

    Airbus has issued All Operators Telex (AOT) A300/78A0023, dated 
April 5, 2002, which describes procedures for deactivating both thrust 
reversers on Model A300 B2 and B4 series airplanes. The Direction 
Generale de l'Aviation Civile (DGAC), which is the airworthiness 
authority for France, classified this AOT as mandatory and issued 
French telegraphic airworthiness directive 2002-189(B), dated April 5, 
2002, to ensure the continued airworthiness of these airplanes in 
France.

Explanation of Change to Emergency AD

    The ``Explanation of Relevant Service Information'' section of the 
emergency AD states, ``The DGAC * * * issued French telegraphic 
airworthiness directive 2001-523(B), dated April 5, 2002, to ensure the 
continued airworthiness of these airplanes in France.'' The number of 
the French telegraphic airworthiness directive as cited in the 
emergency AD is incorrect. The correct number is 2002-189(B). The 
correct number has been cited in the section above as well as in NOTE 4 
of this amendment. The date for the French telegraphic airworthiness 
directive, April 5, 2002, is correct as cited.

FAA's Conclusions

    This airplane model is manufactured in France and is 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 as it pertains to Airbus Model A300 B2 
and B4 series airplanes. The FAA has examined the findings of the DGAC, 
reviewed all available information, and determined that AD action is 
necessary for products of this type design that are certificated for 
operation in the United States.

Explanation of the Requirements of the Rule

    Since the unsafe condition described is likely to exist or develop 
on other airplanes of the same type design registered in the United 
States, the FAA issued emergency AD 2002-08-51 to prevent uncommanded 
in-flight deployment of a thrust reverser, which could result in 
reduced controllability of the airplane. The AD requires deactivating 
both thrust reversers in accordance with the AOT described previously. 
Additionally, this airworthiness directive requires revising the FAA-
approved 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. On an interim basis, this AD includes a penalty 
of five percent of the acceleration-stop distance for takeoffs on wet 
or contaminated runways. This penalty is an estimate that is necessary 
to provide an acceptable level of safety until we receive more 
information and a more precise performance penalty can be established.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make the AD effective immediately by individual notices 
issued on April 8, 2002, to all known U.S. owners and operators of 
Airbus Model A300 B2 and B4 series airplanes equipped with General 
Electric CF6-50 engines. These conditions still exist, and the AD is 
hereby published in the Federal Register as an amendment to section 
39.13 of the Federal Aviation Regulations (14 CFR 39.13) to make it 
effective to all persons.

[[Page 21571]]

Similar AD Action on Other Airplanes

    As stated above, the incident described previously occurred on a 
McDonnell Douglas Model DC-10-30 airplane equipped with General 
Electric CF6-50 engines. The FAA is planning to issue an airworthiness 
directive similar to this one, to require revising the AFM and 
deactivating the thrust reversers under certain conditions on those 
airplanes. Because the identified unsafe condition may be especially 
critical for Airbus Model A300 B2 and B4 series airplanes, the FAA 
finds it appropriate to proceed with this action applying to those 
airplanes now.

Interim Action

    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications shall identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2002-NM-107-AD.'' The postcard will be date-stamped 
and returned to the commenter.

Regulatory Impact

    The regulations adopted herein will 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, may be obtained from the Rules Docket at the 
location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new 
airworthiness directive:

2002-08-51 Airbus: Amendment 39-12728. Docket 2002-NM-107-AD.

    Applicability: Model A300 B2 and B4 series airplanes equipped 
with General Electric CF6-50 engines, certificated in any category.

    Note 1: Airbus Model A300 B4-600 series airplanes (commonly 
referred to as ``A300-600 series airplanes'') are not affected by 
this AD.


    Note 2: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (b) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent uncommanded in-flight deployment of a thrust 
reverser, accomplish the following:

Thrust Reverser Deactivation and AFM Revision

    (a) Within 72 clock hours after the effective date of this AD, 
accomplish paragraphs (a)(1) and (a)(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 Airplane Flight Manual 
(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).)''

Alternative Methods of Compliance

    (b) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate. Operators shall submit their 
requests through an appropriate FAA Principal Maintenance or 
Operations Inspector, as applicable, who may add comments and then 
send it to the Manager, International Branch, ANM-116.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (c) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (d) The deactivation of thrust reversers shall be done in 
accordance with Airbus All Operators Telex A300/78A0023, dated April 
5, 2002. This incorporation by reference was approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51. Copies may be obtained from Airbus Industrie, 1 
Rond Point Maurice

[[Page 21572]]

Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at 
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

    Note 4: The subject of this AD is addressed in French 
telegraphic airworthiness directive 2002-189(B), dated April 5, 
2002.

Effective Date

    (e) This amendment becomes effective on May 6, 2002, to all 
persons except those persons to whom it was made immediately 
effective by emergency AD 2002-08-51, issued April 8, 2002, which 
contained the requirements of this amendment.

    Issued in Renton, Washington, on April 19, 2002.
Lirio Liu-Nelson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-10245 Filed 4-30-02; 8:45 am]
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