AD 2000-13-07

[Federal Register Volume 65, Number 128 (Monday, July 3, 2000)]
[Rules and Regulations]
[Pages 40985-40988]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-16357]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-196-AD; Amendment 39-11806; AD 2000-13-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330 and A340 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A330 and A340 series airplanes. This 
AD requires repetitive detailed visual and ultrasonic inspections of 
the main landing gear (MLG) to detect fatigue cracks, and repair if 
necessary; replacement of certain nose landing gear (NLG) handwheel 
controllers and certain placards with new placards; installation of 
steering angle recording software; and corrective action for exceeding 
certain steering angles. This AD also requires 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 amendment 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 MLG failure due to fatigue cracking, which could 
result in reduced structural capability of the airplane and collapse of 
the MLG.

DATES: Effective August 7, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 7, 2000.

ADDRESSES: 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 Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 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: 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to all Airbus Model A330 and A340 
series airplanes was published in the Federal Register on January 12, 
2000 (65 FR 1833). That action proposed to require repetitive detailed 
visual and ultrasonic inspections of the main landing gear (MLG) to 
detect fatigue cracks, and repair if necessary; replacement of certain 
nose landing gear (NLG) handwheel controllers and 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.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comment received.

Request To Exclude Certain Airplanes From Proposed Actions

    The commenter (an operator) requests that certain airplanes be 
excluded from the actions specified in the proposed AD. (Although the 
proposed rule identifies no affected U.S.-registered airplanes, the 
commenter has since taken delivery of several Model A330 series 
airplanes.) Subsequent to issuance of the proposed rule, the 
manufacturer developed the following production modifications for Model 
A330 and A340 series airplanes (all of which have been installed on the 
commenter's airplanes):

Modification 47487: Introduces scallop on the growth main fitting of 
the main landing gear (MLG)
Modification 47500: Introduces brake steering and control unit (BSCU) 
S8D for the MLG
Modification 47701: Provides for application of markings for maximum 
turning angle (<plus-minus>65 degrees) for towing and pushback of the 
nose landing gear doors
Modification 47787: Introduces ACMS software to record nose wheel 
steering angles exceeding 67 degrees during towing and pushback

FAA Response

    The FAA concurs with the request. The Direction Generale de 
l'Aviation

[[Page 40986]]

Civile (DGAC), which is the airworthiness authority for France, advises 
that the four production modifications are acceptable alternative means 
of compliance with all requirements of the parallel French 
airworthiness directives. Based on the data presented, the FAA has 
revised the applicability of the final rule to remove the inspection 
and modification requirements for airplanes on which all four of the 
referenced production modifications have been installed.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change described 
previously. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    None of the airplanes affected by this action is 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 
inspect the main landing gear; approximately 7 work hours to replace 
the controller; approximately 1 work hour to replace the placards; 
approximately 1 work hour to install the software program; and 
approximately 1 work hour to revise the AFM. The average labor rate is 
$60 per work hour. The manufacturer has previously committed to bearing 
the cost of the necessary parts to accomplish the actions. Based on 
these figures, the cost impact of the inspections required by this AD 
would be $60 per airplane, per inspection cycle, and $660 per airplane 
for the remaining actions.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted.
    Should an operator elect to modify the functional software of the 
brake steering and control unit (BSCU) rather than replace the nose 
wheel steering handwheel controllers, the modification would take 
approximately 1 work hour. Based on this figure, the cost impact of the 
optional modification would be $60 per airplane.

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:

2000-13-07  Airbus Industrie: Amendment 39-11806. Docket 99-NM-196-
AD.

    Applicability: Model A330 and A340 series airplanes, 
certificated in any category, except those on which Airbus 
Modifications 47487, 47500, 47701, and 47787 have been installed in 
production.

    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 (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

[[Page 40987]]

(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 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

    (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 
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

    (m) Except for the repair required by paragraph (c) of this AD: 
The actions shall be done in accordance with the following Airbus 
service bulletins and telex, as applicable.

[[Page 40988]]



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    Airbus service bulletin number          Revision level                    Service bulletin date
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A330-32A3088.........................  02.....................  June 10, 1999.
A340-32A4124.........................  01.....................  November 20, 1998.
A330-32-3091.........................  01.....................  December 2, 1998.
A330-32-3092.........................  02.....................  June 10, 1999.
A340-32-4128.........................  01.....................  December 2, 1998.
A340-32-4131.........................  01.....................  June 10, 1999.
A330-32-3089.........................  Original...............  November 2, 1998.
A340-32-4126.........................  Original...............  November 2, 1998.
A330-31-3033.........................  Original...............  September 13, 1999.
A340-31-4047.........................  Original...............  September 13, 1999.
Flight Operations TELEX 999.0099/98..  Revision 5.............  May 21, 1999.
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    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 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.


    (n) This amendment becomes effective on August 7, 2000.

    Issued in Renton, Washington, on June 22, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-16357 Filed 6-30-00; 8:45 am]
BILLING CODE 4910-13-U