[Federal Register Volume 68, Number 24 (Wednesday, February 5, 2003)]
[Rules and Regulations]
[Pages 5812-5815]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-2146]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-102-AD; Amendment 39-13040; AD 2003-03-16]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-223, -321, -322, and 
-323 Series Airplanes Equipped With Pratt & Whitney Model PW4164, 
PW4168, or PW4168A 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 A330-223, -321, -322, and -323 
series airplanes equipped with Pratt & Whitney Model PW4164, PW4168, or 
PW4168A engines. This action requires modification of the primary 
structure of the engine pylons, and replacement of the thrust reverser 
locking actuators with new, improved locking actuators. This action is 
necessary to prevent reduced structural integrity of the primary 
structure of the engine pylons, and uncommanded deployment of the 
thrust reversers, which could result in reduced controllability of the 
airplane. This action is intended to address the identified unsafe 
condition.

DATES: Effective February 20, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 20, 2003.
    Comments for inclusion in the Rules Docket must be received on or 
before March 7, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-102-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 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

[[Page 5813]]

``Docket No. 2002-NM-102-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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The Direction Generale de l'Aviation Civile 
(DGAC), which is the airworthiness authority for France, notified the 
FAA that an unsafe condition may exist on certain Airbus Model A330-
223, -321, -322, and -323 series airplanes equipped with Pratt & 
Whitney Model PW4164, PW4168, or PW4168A engines. The DGAC advises that 
engine fan blade-out tests performed by the engine manufacturer, Pratt 
&Whitney, have shown that the loads used for certification of the 
engines were underestimated. In the event of an engine fan blade-out, 
the induced loads could lead to reduced structural integrity of the 
primary structure of the engine pylons, and uncommanded deployment of 
the thrust reversers. This condition, if not corrected, could result in 
reduced controllability of the airplane.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A330-54-3016, Revision 01, dated 
August 7, 2000, which describes procedures for the modification of the 
primary structure of the engine pylons. The modification includes, 
among other actions, replacing the stainless steel screws at rib 8B and 
rib 12 with Inconel screws, and replacing the stainless steel screws 
located on the lateral panel seam of the lower spar between rib 8C and 
rib 10 with stainless steel screws of the next-higher-nominal diameter.
    Airbus has also issued Service Bulletin A330-78-3011, dated 
December 14, 1999, which describes procedures for the replacement of 
the thrust reverser locking actuators with new, improved locking 
actuators.
    Accomplishment of the actions specified in these service bulletins 
is intended to adequately address the identified unsafe condition. The 
DGAC classified these service bulletins as mandatory and issued French 
airworthiness directive 2000-237-123(B) R1, dated December 12, 2001, in 
order to assure the continued airworthiness of these airplanes in 
France.
    Airbus Service Bulletin A330-78-3011, dated December 14, 1999, 
references Pratt & Whitney Service Bulletin PW4G-100-78-71, dated 
September 24, 1999, as an additional source of service information for 
accomplishment of the replacement of the thrust reverser locking 
actuators.

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 21.19) 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 the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design that may be 
registered in the United States at some time in the future, this AD is 
being issued to prevent the reduced structural integrity of the primary 
structure of the engine pylons, and uncommanded deployment of the 
thrust reversers, which could result in reduced controllability of the 
airplane. This AD requires accomplishment of the actions specified in 
the service bulletins described previously, except as discussed below.

Differences Between this AD and the French Airworthiness Directive

    This AD differs from the parallel French airworthiness directive in 
that it will not require repetitive visual inspections of the fan 
blades at intervals not to exceed 500 engine hours, or an ultrasonic 
inspection of the attachment area of the fan blade root before the 
accumulation of 5,000 parts cycles since new, or within 500 parts 
cycles after the effective date of the French airworthiness directive. 
These inspections are not associated with any known unsafe condition. 
The DGAC required these inspections to minimize the possibility of a 
fan blade-off event, pending the retrofit of the modifications in 
paragraph 3 of the French airworthiness directive. All Airbus Model 
A330-223, -321, -322, and -323 series airplanes of U.S. registry were 
delivered with the modifications installed.
    The French airworthiness directive defers implementation of the 
mandatory actions (i.e., modification of the engine pylon and 
replacement of the thrust reverser locking actuators) for a period of 
time by requiring the inspections described in the preceding paragraph. 
The compliance time for accomplishment of the mandatory actions is 
before the accumulation of 8,000 flight cycles since new, or before 
August 1, 2004, whichever occurs first. The DGAC advises that if the 
inspections in the preceding paragraph are not mandated, the 
modifications must be accomplished in a timeframe comparable to that of 
the inspections. Therefore, this AD requires accomplishment of the 
mandatory actions within 500 engine hours or six months after the 
effective date of this AD, whichever occurs later.
    Operators should note that, unlike the French airworthiness 
directive, this AD will not require the replacement of the pylon aft 
mount nuts and bolts since the manufacturer has confirmed to the FAA 
that all pylon aft mount nuts and bolts made of MP159 material have 
already been replaced. Additionally, the French airworthiness directive 
requires replacement of the pylon front mount bolts made of MP159 
material. The FAA has determined through review of data provided by the 
engine manufacturer that repetitive inspection of front mount bolts 
made of MP159 material addresses the unsafe condition. As discussed 
below, the FAA previously issued two other ADs that require these 
actions.
    These differences have been coordinated with and acknowledged by 
the DGAC.

Other Relevant Rulemaking

    The FAA has previously issued two other ADs that concern the pylon 
aft and forward mount nuts and bolts on Airbus airplanes:
    1. AD 2000-25-53, amendment 39-12051 (65 FR 82259, December 28, 
2000), requires repetitive inspections for cracks or other damage of 
pylon aft mount nuts and bolts made of MP159 material.
    2. AD 2000-16-02, amendment 39-11856 (65 FR 49730, August 15, 
2000), requires repetitive inspections and

[[Page 5814]]

torque checks for loose or broken pylon forward mount bolts made from 
INCO 718 material and establishes a new life limit for these bolts. The 
AD also requires repetitive inspections of pylon forward mount bolts 
made from MP159 material.
    However, this AD will not affect the current requirements of either 
of those previously issued ADs.

Cost Impact

    The FAA estimates that 9 airplanes of U.S. registry will be 
affected by this AD. The FAA has been advised that the 9 affected 
airplanes have been modified in accordance with the requirements of 
this AD. Therefore, currently, this AD action imposes no additional 
economic burden on any U.S. operator.
    However, should an unmodified airplane be imported and placed on 
the U.S. Register in the future, it will take approximately 51 work 
hours per airplane to accomplish the actions, at an average labor rate 
of $60 per work hour. Required parts will be supplied by the 
manufacturer to the operators at no cost. Based on these figures, the 
cost impact of the AD is estimated to be $3,060 per airplane.

Determination of Rule's Effective Date

    Since this AD action does not affect any airplane that is currently 
on the U.S. registry, it has no adverse economic impact and imposes no 
additional burden on any person. Therefore, prior notice and public 
procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and 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:
    [sbull] 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.
    [sbull] For each issue, state what specific change to the proposed 
AD is being requested.
    [sbull] 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 2002-NM-102-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.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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:

2003-03-16 Airbus: Amendment 39-13040. Docket 2002-NM-102-AD.

    Applicability: Airbus Model A330-223, -321, -322, and -323 
series airplanes, certificated in any category, equipped with Pratt 
& Whitney Model PW4164, PW4168, or PW4168A engines; except those 
airplanes on which all of the following modifications have been 
installed:

--Modification 46147 (reference Airbus Service Bulletin A330-54-
3016, Revision 01, dated August 7, 2000);
--Modification 46948 (reference Airbus Service Bulletin A330-71-
3012, Revision 01, dated August 25, 2000), or Modification 49419 
(reference Airbus Service Bulletin A330-71-3015, Revision 01, dated 
March 19, 2002);
--Modification 46383 (reference Airbus Service Bulletin A330-71-
3009, Revision 02, dated August 31, 2001); and
--Modification 47341 (reference Airbus Service Bulletin A330-78-
3011, dated December 14, 1999).

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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 (e) 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 reduced structural integrity of the primary structure 
of the engine pylons, and uncommanded deployment of the thrust 
reversers, which could result in reduced controllability of the 
airplane, accomplish the following:

Modification of the Engine Pylon Primary Structure

    (a) Prior to the accumulation of 500 flight cycles on the engine 
or 6 months after the effective date of this AD, whichever occurs 
later, modify the primary structure of the engine pylon by 
accomplishing all of the actions specified in the Accomplishment

[[Page 5815]]

Instructions of Airbus Service Bulletin A330-54-3016, Revision 01, 
dated August 7, 2000, per the service bulletin.
    (b) Modifications accomplished before the effective date of this 
AD, per Airbus Service Bulletin A330-54-3016, dated July 15, 1999, 
are considered acceptable for compliance with the applicable 
modification required by this AD.

Replacement of Thrust Reverser Locking Actuators

    (c) Within 500 hours on the engine or 6 months after the 
effective date of this AD, whichever occurs later, replace the 
thrust reverser locking actuators on engine 1 and engine 2 with new 
and improved actuators, per Airbus Service Bulletin A330-78-3011, 
dated December 14, 1999.

    Note 2: Airbus Service Bulletin A330-78-3011, dated December 14, 
1999, references Pratt & Whitney Service Bulletin PW4G-100-78-71, 
dated September 24, 1999, as an additional source of service 
information for accomplishment of the replacement of the thrust 
reverser locking actuators.

Parts Installation

    (d) As of the effective date of this AD, no person may install a 
locking actuator having part number 1610000-11 or -13, on any 
airplane.

Alternative Methods of Compliance

    (e) 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 Inspector, 
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

    (f) 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

    (g) Unless otherwise specified in this AD, the actions shall be 
done in accordance with Airbus Service Bulletin A330-54-3016, 
Revision 01, dated August 7, 2000; and Airbus Service Bulletin A330-
78-3011, dated December 14, 1999; as applicable. 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 4: The subject of this AD is addressed in French 
airworthiness directive 2000-237-123(B) R1, dated December 12, 2001.

Effective Date

    (h) This amendment becomes effective on February 20, 2003.

    Issued in Renton, Washington, on January 24, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-2146 Filed 2-4-03; 8:45 am]
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