[Federal Register Volume 65, Number 8 (Wednesday, January 12, 2000)]
[Proposed Rules]
[Pages 1833-1836]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-600]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-196-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330 and A340 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to all Airbus Model A330 and A340 
series airplanes. This proposal would require repetitive detailed 
visual and ultrasonic inspections of the main landing gear (MLG) to 
detect fatigue cracks; and repair, if necessary. This proposal also 
would require replacement of certain nose landing gear (NLG) handwheel 
controllers with new controllers; replacement of certain placards with 
new placards; installation of steering angle recording software; 
corrective action for exceeding certain steering angles; and an AFM 
revision to limit the nose wheel steering angle for pushback and towing 
and to limit the nose wheel steering for powered turns. This proposal 
is prompted by issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. The actions 
specified by the proposed AD are intended to prevent MLG failure due to 
fatigue cracking, which could result in reduced structural capability 
of the airplane and collapse of the MLG.

DATES: Comments must be received by February 11, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-196-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.
    The service information referenced in the proposed rule 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.

FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 99-NM-196-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 99-NM-196-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France,

[[Page 1834]]

notified the FAA that an unsafe condition may exist on all Airbus Model 
A330 and A340 series airplanes. The DGAC advises that a right main 
landing gear (MLG) of a Model A340 failed during landing. Investigation 
revealed a fatigue crack had initiated in the upper part of the MLG 
main fitting cylindrical barrel. This fatigue crack is a result of 
repetitive loading during high steering and/or towing angles when 
turning. This condition, if not corrected, could result in MLG failure 
due to fatigue cracking, which could result in reduced structural 
capability of the airplane and collapse of the MLG.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A330-32A3088, Revision 02, dated 
June 10, 1999 (for Model A330 series airplanes), and Service Bulletin 
A340-32A4124, Revision 01, dated November 20, 1998, which describe 
procedures for repetitive detailed visual and ultrasonic inspection of 
the MLG to detect fatigue cracks; and corrective actions, if necessary. 
The corrective actions involve a detailed magnetic particle inspection 
of the MLG to detect fatigue cracks, and repair, if necessary.
    Airbus also has issued Service Bulletin A330-32-3089, dated 
November 2, 1998 (for Model A330 series airplanes), and Service 
Bulletin Service Bulletin A340-32-4126, dated November 2, 1998 (for 
Model A340 series airplanes), which describe procedures for replacement 
of placards on the left-and right-hand sides of the aft mechanically-
operated nose landing gear doors with new placards.
    Airbus also has issued Flight Operations TELEX (FOT) 999.0099/98, 
Revision 5, dated May 21, 1999, which describes procedures for revising 
the procedures of the Flight Crew Operating Manual to limit the nose 
wheel steering angle for pushback and towing and to limit the nose 
wheel steering for powered turns.
    Airbus also has issued Service Bulletin A330-32-3091, Revision 01, 
dated December 2, 1998 (for Model A330 series airplanes), and Service 
Bulletin A340-32-4128, Revision 01, dated December 2, 1998 (for Model 
A340 series airplanes), which describe procedures for replacement of 
nose wheel steering controllers with new controllers.
    In addition, Airbus has issued Service Bulletin A330-32-3092, 
Revision 02, dated June 10, 1999 (for Model A330 series airplanes), and 
Service Bulletin A340-32-4131, Revision 01, dated June 10, 1999 (for 
Model A340 series airplanes), which describe procedures for 
modification of the functional software of the brake steering and 
control unit (BSCU). This modification can be utilized as an 
alternative for the replacement of the nose wheel steering controllers 
recommended by Airbus Service Bulletin A330-32-3091, Revision 01, dated 
December 2, 1998 (for Model A330 series airplanes), and Service 
Bulletin A340-32-4128, Revision 01, dated December 2, 1998 (for Model 
A340 series airplanes).
    Airbus also has issued Service Bulletin A330-31-3033, dated 
September 13, 1999 (for Model A330 series airplanes), and Service 
Bulletin A340-31-4047, dated September 13, 1999 (for Model A340 series 
airplanes), which describe procedures for installation of a software 
program that automatically records all nose wheel steering angle 
exceedance above 63 degrees into the Aircraft Condition Monitoring 
System (ACMS). This installation includes modification of the new setup 
database software by adding the existing operator customized version; 
and uploading the setup database software to the data management unit 
(DMU).
    Accomplishment of the actions specified in the service information 
is intended to adequately address the identified unsafe condition. The 
DGAC classified this service information as mandatory and issued French 
airworthiness directives 1998-475-103(B)R1, 1998-473-083(B)R1, and 
1999-160-096(B); all dated April 21, 1999; 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 Proposed 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, the proposed AD would require accomplishment of 
the actions specified in the service information described previously, 
except as discussed below. The proposed AD also would require that 
operators report results of inspection findings to Airbus.

Differences Between Proposed Rule, Service Bulletins, and French 
Airworthiness Directives

    Operators should note that, although the service bulletins and the 
French airworthiness directives specify that the manufacturer may be 
contacted for disposition of certain repair conditions, this proposal 
would require the repair of those conditions to be accomplished in 
accordance with a method approved by the FAA or the DGAC (or its 
delegated agent).
    Operators should also note that the parallel French airworthiness 
directives require a revision of the Flight Crew Operating Manual 
(FCOM) to limit the nose wheel steering angle for pushback and towing 
and to limit the nose wheel steering for powered turns. However, for 
U.S. operators, the FCOM is not approved and required by the FAA, 
whereas the Airplane Flight Manual is approved and required by the FAA. 
Therefore, the proposed AD would require a revision to the AFM instead 
of a revision to the FCOM.

Cost Impact

    None of the airplanes affected by this action are on the U.S. 
Register. All airplanes included in the applicability of this rule 
currently are operated by non-U.S. operators under foreign registry; 
therefore, they are not directly affected by this AD action. However, 
the FAA considers that this rule is necessary to ensure that the unsafe 
condition is addressed in the event that any of these subject airplanes 
are imported and placed on the U.S. Register in the future.
    Should an affected airplane be imported and placed on the U.S. 
Register in the future, it would require approximately 1 work hour to 
accomplish the proposed inspection of the required main landing gear; 
approximately 7 work hours to accomplish the proposed replacement of 
the controller; approximately 1 work hour to accomplish the proposed 
placard replacements; approximately 1 work hour to accomplish the 
proposed installation of the software program; and approximately 1 work 
hour to accomplish the proposed AFM revision; at an average labor rate 
of $60 per work hour. The manufacturer has previously committed to 
bearing the cost of the necessary parts to accomplish the proposed 
actions. Based on these figures, the cost impact of this AD

[[Page 1835]]

would be $60 per airplane, per inspection cycle, and $600 per airplane 
for the remaining actions.
    Should an operator elect to accomplish the modification of the 
functional software of the brake steering and control unit (BSCU) 
instead of replacing the nose wheel steering handwheel controllers with 
new controllers, the modification would take approximately 1 work hour 
to accomplish. Based on this figure, the cost impact of the optional 
modification would be $60 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the proposed requirements 
of this AD action, and that no operator would accomplish those actions 
in the future if this AD were not adopted.

Regulatory Impact

    The regulations proposed herein would not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this 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) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

Airbus Industrie: Docket 99-NM-196-AD.

    Applicability: All Model A330 and A340 series airplanes, 
certificated in any category.

    Note 1: 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 (k) 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 main landing gear (MLG) failure due to fatigue 
cracking, which could result in reduced structural capability of the 
airplane and collapse of the MLG, accomplish the following:

Inspection of the MLG

    (a) Prior to the accumulation of 800 total landings on the MLG, 
or within 120 landings after the effective date of this AD, 
whichever occurs later, perform detailed visual and ultrasonic 
inspections of the MLG to detect fatigue cracks, as specified in 
either paragraph (a)(1) or (a)(2) of this AD, as applicable.
    (1) For Model A330 series airplanes: Accomplish the detailed 
visual and ultrasonic inspections, in accordance with Airbus Service 
Bulletin A330-32A3088, Revision 02, dated June 10, 1999.

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

    Note 3: Detailed visual and ultrasonic inspections accomplished 
prior to the effective date of this AD in accordance with Airbus 
Service Bulletin A330-32A3088, dated October 16, 1998; or Revision 
01, dated November 20, 1998; are acceptable methods of compliance 
for the inspection requirements of paragraph (a)(1) of this AD.

    (2) For Model A340 series airplanes: Accomplish the detailed 
visual and ultrasonic inspections in accordance with Airbus Service 
Bulletin A340-32A4124, Revision 01, dated November 20, 1998.

    Note 4: Detailed visual and ultrasonic inspections accomplished 
prior to the effective date of this AD in accordance with Airbus 
Service Bulletin A340-32A4124, dated October 16, 1998, are 
acceptable methods of compliance for the inspection requirements of 
paragraph (a)(2) of this AD.

Repetitive Inspections

    (b) If no crack is detected during the inspection required by 
paragraph (a)(1) or (a)(2) of this AD: Repeat the detailed visual 
and ultrasonic inspections thereafter at intervals not to exceed 120 
landings.

Corrective Actions

    (c) If any cracking is detected during any inspection required 
by paragraph (a) or (b) of this AD: Prior to further flight, perform 
a detailed magnetic particle inspection of the MLG to detect fatigue 
cracks, in accordance with Airbus Service Bulletin A330-32A3088, 
Revision 02, dated June 10, 1999, or Airbus Service Bulletin A340-
32A4124, Revision 01, dated November 20, 1998, as applicable; and 
repair in accordance with a method approved by the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
or the Direction Generale de l'Aviation Civile (DGAC) (or its 
delegated agent). For a repair method to be approved by the Manager, 
International Branch, ANM-116, as required by this paragraph, the 
Manager's approval letter must specifically reference this AD.

Reporting

    (d) Within 10 days after accomplishing any inspection required 
by paragraph (a), (b) or (c) of this AD, report the inspection 
results (both positive and negative) to Airbus Industrie at fax 
33(0) 5 61 93 32 73. Information collection requirements contained 
in this regulation have been approved by the Office of Management 
and Budget (OMB) under the provisions of the Paperwork Reduction Act 
of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control 
Number 2120-0056.

Replacement of Nose Wheel Steering Handwheel Controllers or Software 
Modification

    (e) Within 20 days after the effective date of this AD, replace 
the nose wheel steering handwheel controllers with new controllers, 
or modify the functional software of the brake steering and control 
unit (BSCU), as specified in either paragraph (e)(1) or (e)(2) of 
this AD, as applicable.
    (1) For Model A330 series airplanes: Replace the controllers in 
accordance with Airbus Service Bulletin A330-32-3091, Revision 01, 
dated December 2, 1998, or modify the functional software of the 
BSCU in accordance with Airbus Service Bulletin A330-32-3092, 
Revision 02, dated June 10, 1999.

    Note 5: Replacement of nose wheel steering handwheel controllers 
with new controllers accomplished prior to the effective date of 
this AD in accordance with Airbus Service

[[Page 1836]]

Bulletin A330-32-3091, dated November 19, 1998, is an acceptable 
method of compliance for the replacement requirements of paragraph 
(e)(1) of this AD.

    Note 6: Modification of the functional software of the BSCU 
accomplished prior to the effective date of this AD in accordance 
with Airbus Service Bulletin A330-32-3092, dated December 18, 1998; 
or Revision 01, dated February 24, 1999; is an acceptable method of 
compliance for the software modification requirements of paragraph 
(e)(1) of this AD.

    (2) For Model A340 series airplanes: Replace the controllers in 
accordance with Airbus Service Bulletin A340-32-4128, Revision 01, 
dated December 2, 1998, or modify the functional software of the 
BSCU in accordance with Airbus Service Bulletin A340-32-4131, 
Revision 01, dated June 10, 1999.

    Note 7: Replacement of nose wheel steering handwheel controllers 
with new controllers accomplished prior to the effective date of 
this AD in accordance with Airbus Service Bulletin A340-32-4128, 
dated November 19, 1998, is an acceptable method of compliance for 
the replacement requirements of paragraph (e)(2) of this AD.

    Note 8: Modification of the functional software of the BSCU 
accomplished prior to the effective date of this AD in accordance 
with Airbus Service Bulletin A340-32-4131, dated February 24, 1999, 
is an acceptable method of compliance for the software modification 
requirements of paragraph (e)(2) of this AD.

Replacement of Placards on Mechanically-Operated Nose Landing Gear 
Doors

    (f) Within 20 days after the effective date of this AD, replace 
the placards on the left-and right-hand sides of the aft 
mechanically-operated nose landing gear doors with new placards, as 
specified in either paragraph (f)(1) or (f)(2) of this AD, as 
applicable.
    (1) For Model A330 series airplanes: Replace placards in 
accordance with Airbus Service Bulletin A330-32-3089, dated November 
2, 1998.
    (2) For Model A340 series airplanes: Replace placards in 
accordance with Airbus Service Bulletin A340-32-4126, dated November 
2, 1998.

Installation of a Software Program

    (g) Within 20 days after the effective date of this AD, 
accomplish either paragraph (g)(1) or (g)(2) of this AD, as 
applicable.
    (1) For Model A330-200 series airplanes: Install a software 
program that automatically records all nose wheel steering angle 
exceedance above 63 degrees into the Aircraft Condition Monitoring 
System (ACMS) [i.e., modify the new setup database software by 
adding the existing operator customized version; and upload the 
setup database software to the data management unit (DMU)] in 
accordance with Airbus Service Bulletin A330-31-3033, dated 
September 13, 1999.
    (2) For Model A330-300 and Model A340 series airplanes: Install 
a software program that automatically records all nose wheel 
steering angle exceedance above 67 degrees into the ACMS (i.e. 
modify the new setup database software by adding the existing 
operator customized version; and upload the setup database software 
to the DMU) in accordance with Airbus Service Bulletin A330-31-3033, 
dated September 13, 1999 (for Model A330-300 series airplanes), or 
Airbus Service Bulletin A340-31-4047, dated September 13, 1999 (for 
Model A340 series airplanes); as applicable.

Incorporation of Ground and Crew Operating Procedures

    (h) Within 20 days after the effective date of this AD, revise 
the Limitations Section of the FAA-approved Airplane Flight Manual 
(AFM) by inserting the procedures to incorporate ground operating 
procedures to limit the nose wheel steering angle for pushback and 
towing and to limit nose wheel steering for powered turns, in 
accordance with Flight Operations TELEX (FOT) 999.0099/98, Revision 
5, dated May 21, 1999.

Corrective Actions for Exceedance of Nose Wheel Steering Angle

    (i) For Model A330-200 series airplanes: If after 20 days from 
the effective date of this AD, a 63-degree hand wheel steering is 
exceeded, a 63 degrees is recorded on the ACMS, or a 60-degree 
steering is exceeded during towing or pushback, within 4 landings 
after each occurrence, accomplish the actions required by paragraph 
(a) of this AD.
    (j) For Model A330-300 and Model A340 series airplanes: If after 
20 days from the effective date of this AD, a 65-degree hand wheel 
steering is exceeded, a 67 degrees is recorded on the ACMS, or a 60-
degree steering is exceeded during towing or pushback; within 4 
landings after each occurrence, accomplish paragraph (j)(1) and 
(j)(2) of this AD, as applicable.
    (1) Accomplish the actions required by paragraph (a) of this AD.
    (2) For airplanes on which Airbus Modification 46804 has been 
accomplished: Reinstall a positive stop and re-rig the tiller as 
specified in either paragraph (j)(2)(i) or (j)(2)(ii) of this AD, as 
applicable.
    (i) For Model A330-300 series airplanes: Reinstall a stop and 
re-rig in accordance with Airbus Service Bulletin A330-32-3091, 
Revision 01, dated December 2, 1998.
    (ii) For Model A340 series airplanes: Reinstall a stop and re-
rig in accordance with Airbus Service Bulletin A340-32-4128, 
Revision 01, dated December 2, 1998.

Alternative Methods of Compliance

    (k) 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. 
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 9: 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

    (l) 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.

    Note 10: The subject of this AD is addressed in French 
airworthiness directives 1998-475-103(B)R1; 1998-473-083(B)R1; and 
1999-160-096(B); all dated April 21, 1999.

    Issued in Renton, Washington, on January 5, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-600 Filed 1-11-00; 8:45 am]
BILLING CODE 4910-13-U