Airworthiness Directives; Airbus Model A319, A320, and A321 Series Airplanes

[Federal Register Volume 64, Number 245 (Wednesday, December 22, 1999)]
[Proposed Rules]
[Pages 71696-71698]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-33169]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-331-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319, A320, and A321 
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 certain Airbus Model A319, A320, 
and A321 series airplanes. This proposal would require a one-time 
general visual inspection to determine the part number and serial 
number of the spoiler servocontrol, and corrective action, if 
necessary. 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 failure of the spoiler servocontrol piston rod, which could 
result in reduced controllability of the airplane.

DATES: Comments must be received by January 21, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-331-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-331-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-331-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, notified the FAA that an unsafe 
condition may exist on certain Airbus Model A319, A320, and A321 series 
airplanes. The DGAC advises that several cases of spoiler servocontrol 
piston rod breakage have been reported. As a result, and in almost 
every case, the associated hydraulic system did not function correctly 
and the spoilers were extended in flight to the zero hinge moment 
position. Analysis determined that the piston rod breakage was due to 
excessive misalignment of the actuator housing backface. Failure of the 
spoiler servocontrol piston rod, if not corrected, could result in 
failure of the associated hydraulic system and consequent reduced 
controllability of the airplane.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletins A320-27-1126, dated April 26, 
1999 (for Model A320 series airplanes); and A320-27-1127, dated April 
26, 1999, and Revision 01, dated October 6, 1999 (for Model A319 and 
A321 series airplanes). The service bulletins describe procedures to 
visually inspect the part number and serial number of the installed 
spoiler servocontrol. For certain serial numbers, the servocontrol must 
be replaced. For certain other serial numbers, the servocontrol must be 
re-identified. Revision 01 of Service Bulletin A320-27-1127 is 
essentially the same as the original issue except that the effectivity 
has been updated. Accomplishment of the actions specified in the 
service bulletins is intended to adequately address the identified 
unsafe condition. The DGAC classified these service bulletins as 
mandatory and issued French airworthiness directive 1999-362-139(B), 
dated September 8, 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 
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. 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

[[Page 71697]]

type design registered in the United States, the proposed AD would 
require accomplishment of the actions specified in the service 
bulletins described previously.

Cost Impact

    The FAA estimates that 210 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 2 work 
hours per airplane to accomplish the proposed inspection, and that the 
average labor rate is $60 per work hour. Based on these figures, the 
cost impact of the proposed AD on U.S. operators is estimated to be 
$25,200, or $120 per airplane.
    Should an operator be required to accomplish the modification, it 
will take approximately 4 work hours per airplane, at an average labor 
rate of $60 per work hour. The cost of required parts would be free of 
charge. Based on these figures, the cost impact of the modification is 
estimated to be $240 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-331-AD.

    Applicability: The following models, certificated in any 
category, excluding those on which Airbus Service Bulletin A320-27-
1126, dated April 26, 1999 (for Model A319 and 321 series 
airplanes); or A320-27-1127, dated April 26, 1999, or Revision 01, 
dated October 6, 1999 (for Model A320 series airplanes); has been 
accomplished:
    •  Model A319 series airplanes, serial numbers (S/N) 0546 
through 0972 inclusive;
    •  Model A320 series airplanes, S/N 0002 through 0842 
inclusive, 0846 through 0859 inclusive, 0865, 0866, and 0872 through 
0960 inclusive; and
    •  Model A321 series airplanes, S/N 0364 through 0974 
inclusive.

    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 (c) 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 failure of the servocontrol piston rod, which could 
result in reduced controllability of the airplane, accomplish the 
following:

Inspection

    (a) At the applicable time specified by paragraph (a)(1) or 
(a)(2) of this AD: Perform a general visual inspection to determine 
the part number and serial number for the spoiler servocontrols, in 
accordance with Airbus Service Bulletin A320-27-1126, dated April 
26, 1999 (for Model A319 and A321 series airplanes); or Airbus 
Service Bulletin A320-27-1127, dated April 26, 1999, or Revision 1, 
dated October 6, 1999 (for Model A320 series airplanes); as 
applicable. If the part number and serial number are identified in 
paragraph 2.B.(1)(b) of the Accomplishment Instructions of the 
applicable service bulletin, prior to further flight, perform 
applicable corrective actions (including removal, reidentification 
of the servocontrol, and replacement of the servocontrol with a 
modified part) as specified in the applicable service bulletin.
    (1) For Model A319 and A321 series airplanes: Inspect within 2 
months after the effective date of this AD.
    (2) For Model A320 series airplanes: Inspect within 28 months 
after the effective date of this AD.

    Note 2: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

    (b) As of the effective date of this AD, no person shall install 
on any airplane a spoiler servocontrol having part number 31077-050, 
31077-060, or 31077-110; and S/N 0001 to 3499, except those serial 
numbers excluded in paragraph 2.B.(1)(b)1 of the Accomplishment 
Instructions in Airbus Service Bulletin A320-27-1126, dated April 
26, 1999; unless that servocontrol has been inspected, and 
corrective actions have been performed, in accordance with the 
requirements of this AD.

Alternative Methods of Compliance

    (c) 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

    (d) 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.

    Note 4: The subject of this AD is addressed in French 
airworthiness directive 1999-362-139(B), dated September 8, 1999.


[[Page 71698]]


    Issued in Renton, Washington, on December 16, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-33169 Filed 12-21-99; 8:45 am]
BILLING CODE 4910-13-U