[Federal Register Volume 66, Number 88 (Monday, May 7, 2001)]
[Rules and Regulations]
[Pages 22908-22910]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-10591]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-68-AD; Amendment 39-12210; AD 2001-09-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310-324, A310-325, and 
A300 B4-622R Series Airplanes Equipped with Pratt & Whitney PW4000 
Series Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Airbus Model A310-324, A310-325, and A300 B4-
622R series airplanes equipped with Pratt & Whitney PW4000 series 
engines. This action requires revising the Airplane Flight Manuals 
(AFM) for the Model A310 and Model A300-600 series airplanes. This 
action is necessary to prevent acceleration and climb performance less 
than that specified in the AFM, which could result in runway overruns 
or impact with obstacles or terrain. This action is intended to address 
the identified unsafe condition.

DATES: Effective May 22, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 22, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before June 6, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket Number 2001-NM-68-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal 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. 2001-NM-68-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 service information referenced in this AD 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, ANM-
116, International Branch, FAA, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The FAA has received reports that Pratt & 
Whitney Model PW4000 series engines with certain early-production fan 
blades (Phase 0/1, FB2B or FB2T) installed on Airbus Model A310-324, 
A310-325, and A300 B4-622R series airplanes do not produce the amount 
of thrust indicated in the AFM. This thrust shortfall is due to erosion 
of the fan blade's leading edge. The flight crew has no indication of 
this shortfall in thrust. This condition results in acceleration and 
climb performance less than that specified in the AFM, which, if not 
corrected, could result in an overrun of the runway or impact with an 
obstacle or terrain.

Explanation of Relevant Service Information

    The Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, has requested that Airbus prepare 
revisions to the AFM to take into account the reduction in performance 
associated with PW4000 series engines fitted with early-production fan 
blades and to incorporate the necessary adjustments in performance. 
Those revisions are expected to be available from Airbus in mid-2001. 
Meanwhile, Airbus has issued the following Temporary Revisions (TR) to 
the AFM, each dated January 22, 2001:

A310 Flight Manual TR 5.03.00/01 (for Airbus Model A310-324 series 
airplanes);
A310 Flight Manual TR 5.03.00/02 (for Airbus Model A310-325 series 
airplanes); and
A300-600 Flight Manual TR 5.03.00/01 (for Airbus Model A300 B4-622R 
series airplanes).

    These TR's contain performance adjustments for the AFM for Model 
A310-324, A310-325, and A300 B4-622R series airplanes equipped with one 
or more Pratt & Whitney Model PW4000 series engine with early-
production fan blades. The DGAC classified these TR's as mandatory and 
issued French airworthiness directive 2001-086(B),

[[Page 22909]]

dated March 7, 2001, in order to assure the continued airworthiness of 
these airplanes in France.

FAA's Conclusions

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
Sec. 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. 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 Requirements of Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, this AD is being issued to prevent acceleration 
and climb performance less than that specified in the AFM, which could 
result in runway overruns or impact with obstacles or terrain. This AD 
requires revising the Performance section of the FAA-approved AFM's for 
Model A310-324, A310-325, and 300 B4-622R series airplanes to 
incorporate certain adjustments in performance.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

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.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
     For each issue, state what specific change to the AD is 
being requested.
     Include justification (e.g., reasons or data) for each 
request.
    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 2001-NM-68-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:

2001-09-05  Airbus Industrie: Amendment 39-12210. Docket 2001-NM-68-
AD.

    Applicability: Model A310-324, A310-325, and A300 B4-622R series 
airplanes; certificated in any category; equipped with Pratt & 
Whitney PW4000 series engines, except for airplanes fitted with 
current-production FB2C fan blades (Phase 3 fan blades) on both 
engines.

    Note 1: Airbus Modification 10925 installs Phase 3 engines, and 
these are equipped with FB2C (Phase 3) fan blades. Therefore, this 
AD is not applicable to airplanes with that modification.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent acceleration and climb performance less than that 
specified in the Airplane Flight Manual (AFM), which could result in 
runway overruns or impact with obstacles or terrain, accomplish the 
following:

AFM Revision

    (a) For Model A310-324 and -325 series airplanes: Within 30 days 
after the effective date of this AD, revise the FAA-approved AFM to 
incorporate specified adjustments in performance by inserting the 
following Airbus A310 Flight Manual Temporary Revisions (TR), all 
dated January 22, 2001, as applicable, into the Performance section 
of the AFM: 5.03.00/01 (for Airbus Model A310-324 series airplanes); 
or 5.03.00/02 (for Airbus Model A310-325 series airplanes).
    (b) For Model A300 B4-622R series airplanes: Within 30 days 
after the effective date of this AD, revise the FAA-approved AFM to 
incorporate specified adjustments in performance by inserting the 
following A300-600 Flight Manual TR, dated January 22, 2001 into the 
Performance section of the AFM: 5.03.00/01 (for Airbus Model A300 
B4-622R series airplanes).
    (c) When the information in the TR's specified in paragraphs (a) 
and (b) of this AD, has been incorporated into FAA-approved general 
revisions of the applicable AFM's,

[[Page 22910]]

the general revisions may be incorporated in the applicable AFM, and 
the TR's may be removed from the AFM's.

Alternative Methods of Compliance

    (d) 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, 
Transport Airplane Directorate, FAA. Operators shall submit their 
requests through an appropriate FAA Principal Operations Inspector, 
who may add comments and then send it to the Manager, International 
Branch.

    Note 2: 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

    (e) Special flight permits may be issued in accordance with 
Secs. 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

    (f) The actions shall be done in accordance with Airbus A310 
Flight Manual Temporary Revision 5.03.00/01, dated January 22, 2001; 
Airbus A310 Flight Manual Temporary Revision 5.03.00/02, dated 
January 22, 2001; and Airbus A300-600 Flight Manual Temporary 
Revision 5.03.00/01, dated January 22, 2001; as applicable. (Note: 
Only the first page to each of these Temporary Revisions are date 
stamped; no other pages of the Temporary Revisions contain the 
revision date.) 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 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 3: The subject of this AD is addressed in French 
airworthiness directive 2001-086(B), dated March 7, 2001.

Effective Date

    (g) This amendment becomes effective on May 22, 2001.

    Issued in Renton, Washington, on April 23, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-10591 Filed 5-4-01; 8:45 am]
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