Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes

[Federal Register Volume 71, Number 10 (Tuesday, January 17, 2006)]
[Rules and Regulations]
[Pages 2455-2457]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-315]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22035; Directorate Identifier 2005-NM-016-AD; 
Amendment 39-14442; AD 2006-01-03]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Airbus Model A300 B2 and B4 series airplanes. This AD requires 
repetitive replacement of the angle of attack (AOA) sensors with new or 
overhauled AOA sensors. This AD also provides an optional terminating 
action for the repetitive replacements. This AD results from reports of 
several false stall warnings associated with stick-shaker activation, 
occurring during take-off. We are issuing this AD to prevent false 
stall warnings associated with stick-shaker activation, which could 
result in increased pilot workload as the pilot tries to determine the 
cause of the stall warning and possible reduction in the pilot's 
ability to control the airplane.

DATES: This AD becomes effective February 21, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of February 21, 
2006.

ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., Nassif Building, 
room PL-401, Washington, DC.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1622; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://dms.dot.gov or in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to all Airbus Model A300 
B2 and B4 series airplanes. That NPRM was published in the Federal 
Register on August 8, 2005 (70 FR 45592). That NPRM proposed to require 
an inspection to determine the part number of all angle of attack (AOA) 
sensors, and repetitive replacement of the AOA sensors with new or 
overhauled AOA sensors if necessary.

Relevant Service Information

    After the NPRM was issued, we received Airbus Service Bulletin 
A300-34-0092, Revision 04, dated April 25, 2005. Revision 03, dated 
November 2, 2004, was referenced as the appropriate source of service 
information for accomplishing the optional terminating action specified 
in paragraph (g) of the NPRM. We have reviewed Revision 04 of the 
service bulletin and have determined that the procedures for replacing 
the Honeywell AOA sensors with ``vane type'' AOA sensors and replacing 
the current detectors in relay boxes 252VU and 107VU with new current 
detectors are identical to the procedures in Revision 03 of the service 
bulletin. Therefore, we have revised paragraph (g) of this AD to 
reference Revision 04 of the service bulletin as the appropriate source 
of service information for accomplishing the optional terminating 
action. We have also moved reference to Revision 03 of the service 
bulletin to paragraph (k) of this AD to give credit for actions done in 
accordance with Revision 03 before the effective date of this AD.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Request To Revise the Applicability

    One commenter, the airplane manufacturer, requests that we limit 
the applicability of the NPRM to certain Airbus Model A300 B2 and B4 
series airplanes equipped with Honeywell angle of attack (AOA) sensors 
having part number 965-4020-007. The commenter states that this matches 
the applicability of French airworthiness directive F-2003-457 R1, 
dated December 22, 2004. As justification for limiting the 
applicability, the commenter asserts that operators can easily trace 
the affected part on their airplanes. The commenter also states that 
limiting the applicability will relieve operators from inspecting 
airplanes, which are not equipped with the affected AOA sensor.
    We do not agree to revise the applicability of this AD. Even if 
operators could easily trace AOA sensors installed on an airplane, this 
AD must be applicable to all Model A300 B2 and B4 series airplanes to 
ensure that an affected AOA sensor is not installed on an airplane 
after the effective date of this AD. However, we have added a provision 
to paragraph (f) of this AD to relieve operators of the inspection 
requirement. Operators may conduct a review of airplane maintenance 
records, instead of doing an inspection, if the part numbers of the AOA 
sensors can positively be determined from that review.

Request To Delete Compliance Time

    The same commenter requests that we delete the compliance time for 
replacing the AOA sensor before further flight, as specified in 
paragraph (f) of the NPRM. The commenter states that it is not possible 
to comply with this compliance time because Airbus Service Bulletin 
A300-34-0176, Revision 01, dated

[[Page 2456]]

February 3, 2004, recommends replacing an affected AOA sensor with an 
overhauled AOA sensor, which would require operators to return the 
affected AOA sensor to the parts manufacturer for overhaul.
    We do not agree. In developing an appropriate compliance time for 
this action, we considered the safety implications, parts availability, 
and normal maintenance schedules for the timely accomplishment of the 
replacement. In consideration of these items, we have determined that 
replacing an affected AOA sensors before further flight after 
inspecting to the determine its part number will ensure an acceptable 
level of safety and allow the replacement to be done during scheduled 
maintenance intervals for most affected operators. Also, we point out 
that paragraph (g) of this AD provides an optional terminating action 
to the repetitive replacements required by paragraph (f) of this AD. 
This terminating action allows operators to replace the affected AOA 
sensors with ``vane type'' AOA sensors and does not require returning 
an affected AOA sensor to the parts manufacturer for overhaul. 
According to the manufacturer, an ample number of ``vane type'' AOA 
sensors will be available to modify the U.S. fleet within the proposed 
compliance time. Furthermore, according to the provisions of paragraph 
(l) of this AD, we may approve requests to adjust the compliance time 
if the request includes data that prove that the new compliance time 
would provide an acceptable level of safety.

Request To Reduce the Compliance Time

    One commenter states that a compliance time of 4,500 flight hours 
or 36 months is too long given that the unsafe condition could result 
in increased pilot workload as the pilot tries to determine the cause 
of the stall warning and possible reduction in the pilot's ability to 
control the airplane. We infer the commenter would like us to reduce 
the compliance time.
    We disagree. After considering all the available information, we 
have determined that the compliance time, as proposed, represents an 
appropriate interval of time for accomplishing the required actions in 
a timely manner within the affected fleet, while still maintaining an 
adequate level of safety. In developing an appropriate compliance time, 
we considered the safety implications, parts availability, and normal 
maintenance schedules for timely accomplishment of the inspection. 
Furthermore, we arrived at the compliance time of 4,500 flight hours or 
36 months, whichever is first, with concurrence from the manufacturer 
and the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France. Reducing the 
compliance time would necessitate (under the provisions of the 
Administrative Procedure Act) reissuing the notice, reopening the 
period for public comment, considering additional comments subsequently 
received, and eventually issuing a final rule. That procedure could 
take as long as four months. We have determined that further delay of 
this AD is inappropriate. However, if additional data are presented 
that would justify a shorter compliance time, we may consider further 
rulemaking on this issue.

Clarification of Alternative Method of Compliance (AMOC) Paragraph

    We have revised this AD to clarify the appropriate procedure for 
notifying the principal inspector before using any approved AMOC on any 
airplane to which the AMOC applies.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD.

                                                 Estimated Costs
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                                           Average                                   Number of
                                  Work      labor                        Cost per      U.S.-
            Action               hours    rate  per        Parts         airplane    registered     Fleet cost
                                             hour                                    airplanes
----------------------------------------------------------------------------------------------------------------
Inspection...................          1        $65  None............          $65           20  $1,300.
Replacement, per replacement           2         65  $3,300 ($1,100          3,430           20  $68,600, per
 cycle.                                               per sensor).                                replacement
                                                                                                  cycle.
Optional terminating action..          7         65  $8,780..........        9,235           20  $184,700.
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Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that this AD:
    (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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

[[Page 2457]]

See the ADDRESSES section for a location to examine the regulatory 
evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2006-01-03 Airbus: Amendment 39-14442. Docket No. FAA-2005-22035; 
Directorate Identifier 2005-NM-016-AD.

Effective Date

    (a) This AD becomes effective February 21, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Airbus Model A300 B2-1A, B2-1C, B2K-
3C, and B2-203 airplanes; and Model A300 B4-2C, B4-103, and B4-203 
airplanes; certificated in any category.

Unsafe Condition

    (d) This AD was prompted by reports of several false stall 
warnings associated with stick-shaker activation, occurring during 
take-off. We are issuing this AD to prevent false stall warnings 
associated with stick-shaker activation, which could result in 
increased pilot workload as the pilot tries to determine the cause 
of the stall warning and possible reduction in the pilot's ability 
to control the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Repetitive Replacements

    (f) Within 4,500 flight hours or 36 months after the effective 
date of this AD, whichever is first: Inspect zone 120 to determine 
the part numbers (P/Ns) of all three angle of attack (AOA) sensors, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-34-0176, Revision 01, dated February 3, 2004. Instead 
of inspecting zone 120 to determine the P/Ns of the AOA sensors, a 
review of airplane maintenance records is acceptable if the P/Ns of 
the AOA sensors can be conclusively determined from that review. If 
no Honeywell AOA sensor having part number (P/N) 965-4020-007 is 
found, then no further action is required by this paragraph. If any 
Honeywell AOA sensor having P/N 965-4020-007 is found, before 
further flight, replace the AOA sensor with a new or overhauled AOA 
sensor having P/N 965-4020-007, in accordance with the service 
bulletin. Repeat the replacement thereafter at intervals not to 
exceed 8,000 flight hours or 96 months, whichever is first. 
Accomplishing the actions specified in paragraph (g) of this AD 
terminates the repetitive replacements.

Optional Terminating Action

    (g) Replacement of all Honeywell AOA sensors having P/N 965-
4020-007 between frame (FR)18 and FR19 with ``vane type'' AOA 
sensors; and replacement of the current detectors in relay boxes 
252VU and 107VU with new current detectors; in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-34-0092, 
Revision 04, dated April 25, 2005; terminate the repetitive 
replacements required by paragraph (f) of this AD.

No Reporting Requirement

    (h) Although Airbus Service Bulletin A300-34-0176, Revision 01, 
dated February 3, 2004, specifies to submit certain information to 
the manufacturer, this AD does not include that requirement.

Parts Installation

    (i) As of the effective date of this AD, no person may install 
an AOA sensor having P/N 965-4020-007 on any airplane, unless it is 
new or overhauled. Thereafter repetitively replace the new or 
overhauled AOA sensor in accordance with paragraph (f) of this AD.

Credit for Previously Accomplished Actions

    (j) Actions done before the effective date of this AD in 
accordance with Airbus Service Bulletin A300-34-0176, dated July 9, 
2003, are acceptable for compliance with the corresponding 
requirements of paragraph (f) of this AD.

Credit for Optional Terminating Action

    (k) Actions done before the effective date of this AD in 
accordance with Airbus Service Bulletin A300-34-092, Revision 2, 
dated July 18, 1985, or Airbus Service Bulletin A300-34-0092, 
Revision 03, dated November 2, 2004, are acceptable for compliance 
with the requirements of paragraph (g) of this AD.

Alternative Methods of Compliance (AMOCs)

    (l)(1) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.
    (2) Before using any AMOC approved in accordance with 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (m) French airworthiness directive F-2003-457 R1, dated December 
22, 2004, also addresses the subject of this AD.

Material Incorporated by Reference

    (n) You must use Airbus Service Bulletin A300-34-0176, Revision 
01, excluding Appendix 01, dated February 3, 2004, to perform the 
actions that are required by this AD, unless the AD specifies 
otherwise. The optional terminating action provided by paragraph (g) 
of this AD, if accomplished, must be done in accordance with Airbus 
Service Bulletin A300-34-0092, Revision 04, dated April 25, 2005. 
The Director of the Federal Register approved the incorporation by 
reference of these documents in accordance with 5 U.S.C. 552(a) and 
1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France, for a copy of this service information. You 
may review copies at the Docket Management Facility, U.S. Department 
of Transportation, 400 Seventh Street, SW., room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on January 5, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-315 Filed 1-13-06; 8:45 am]
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