[Federal Register: July 21, 2005 (Volume 70, Number 139)]
[Rules and Regulations]
[Page 41946-41948]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr21jy05-4]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20500; Directorate Identifier 2004-NM-235-AD;
Amendment 39-14191; AD 2005-15-02]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320-111 Airplanes and
Model A320-200 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) that
applies to certain Airbus Model A320-111 airplanes and Model A320-200
series airplanes. This AD requires post-maintenance bleeding of
accumulated air from, or ground functional testing of, the ram air
turbine (RAT) system; modifying and reidentifying the airborne ground
check module of the RAT system; and replacing the RAT reducer assembly
if applicable. This AD is prompted by reports of unsuccessful in-flight
RAT tests during which a deployed RAT failed to pressurize the blue
hydraulic circuit of the RAT system. We are issuing this AD to prevent
failure of the RAT during an in-flight emergency, which could lead to
loss of hydraulic and electrical power and reduced controllability of
the airplane.
DATES: This AD becomes effective August 25, 2005.
The incorporation by reference of certain publications listed in
the AD is approved by the Director of the Federal Register as of August
25, 2005.
ADDRESSES: For service information identified in this AD, contact
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
Docket: The AD docket contains the proposed AD, comments, and any
final disposition. You can examine the 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 U.S.
Department of Transportation, 400 Seventh Street, SW., room PL-401,
Washington, DC. This docket number is FAA-2005-20500; the directorate
identifier for this docket is 2004-NM-235-AD.
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 FAA proposed to amend 14 CFR part 39
with an AD for Airbus Model A320 series airplanes. That action,
published in the Federal Register on March 8, 2005 (70 FR 11170),
proposed to require post-maintenance bleeding of accumulated air from,
or ground functional testing of, the ram air turbine (RAT) system;
modifying and reidentifying the airborne ground check module of the RAT
system; and replacing the RAT reducer assembly if applicable.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
submitted on the proposed AD.
Support for the Proposed AD
One commenter supports the proposed AD.
Request To Revise Applicability
One commenter requests that we change a part number that was
incorrectly referenced in the applicability of the proposed AD. The
commenter states that part number (P/N) 760106 is incorrect and that it
should be changed to P/N 769106.
We agree with this request. P/N 760106 is a part number that is not
referenced by the Airbus service bulletin; it appeared due to a
typographical error. We have corrected paragraph (c) of the final rule
to read P/N 769106, as specified in the Airbus service bulletin and the
French airworthiness directive.
[[Page 41947]]
Request To Revise Requirement for Bleeding of Blue Hydraulic Circuit
The same commenter requests that we revise the wording of
paragraphs (f) and (g) of the proposed AD. The commenter asserts that
the statement ``after performing any maintenance on the blue hydraulic
circuit'' that appears in paragraphs (f) and (g) is too vague and can
be taken as requiring unnecessary bleeding of the blue hydraulic
circuit. The commenter suggests that we revise this wording to read
``after performing any maintenance that would normally require bleeding
of the blue hydraulic circuit (as instructed by the related AMM
procedure).'' The commenter states that such wording would eliminate
any unneeded maintenance introduced by the proposed AD and still ensure
that, during any in-flight emergency, a RAT system failure does not
occur.
We agree with this request. We always seek to use unambiguous
language and the specified statement could be taken as requiring
unnecessary bleeding of the blue hydraulic circuit. Therefore, to
ensure that bleeding of the blue hydraulic circuit must be performed
only as a necessary part of a maintenance action, we have revised
paragraphs (f) and (g) of the final rule to reflect the commenter's
wording.
Explanation of Change to Applicability
The FAA has revised the applicability of the proposed AD to
identify model designations as published in the most recent type
certificate data sheet for the affected models.
Conclusion
We have carefully reviewed the available data, including the
comments that have been submitted, 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
This AD will affect about 130 airplanes of U.S. registry.
The system bleed/functional test will take about 1 work hour per
airplane, at an average labor rate of $65 per work hour. Based on these
figures, the estimated cost of the required actions for U.S. operators
is $8,450, or $65 per airplane.
The airborne ground check module (AGCM) replacement will take about
2 work hours per airplane, at an average labor rate of $65 per work
hour. Required parts will be supplied at no charge. Based on these
figures, the estimated cost of this action for U.S. operators is
$16,900, or $130 per airplane.
The reducer replacement, for subject airplanes, will take about 1
work hour per airplane, at an average labor rate of $65 per work hour.
Required parts will be supplied at no charge. Based on these figures,
the estimated cost of this action for U.S. operators is $65 per
airplane.
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. 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 FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2005-15-02 Airbus: Amendment 39-14191. Docket No. FAA-2005-20500;
Directorate Identifier 2004-NM-235-AD.
Effective Date
(a) This AD becomes effective August 25, 2005.
Affected ADs
(b) None.
Applicability: (c) This AD applies to Airbus Model A320-111
airplanes and Model A320-200 series airplanes, certificated in any
category; equipped with Hamilton Sundstrand airborne ground check
module (AGCM) having part number 769104, 769105, or 769106
installed; except those airplanes on which Airbus Modification 27189
has been done in production and on which Airbus Modification 28413
has not been done.
Unsafe Condition
(d) This AD was prompted by reports of unsuccessful in-flight
ram air turbine (RAT) tests during which a deployed RAT failed to
pressurize the blue hydraulic circuit of the RAT system. We are
issuing this AD to prevent failure of the RAT system during an in-
flight emergency, which could lead to loss of hydraulic and
electrical power and reduced controllability of 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.
RAT System Bleeding/Functional Test
(f) For airplanes on which maintenance has been performed on the
blue hydraulic circuit as of the effective date of this AD: Within 3
days or 20 flight hours after the effective date of this AD,
whichever occurs first, bleed accumulated air from, or perform a
ground functional test of, the RAT system; by accomplishing all the
actions specified in Airbus All Operators Telex (AOT) A320-29A1112,
Revision 01, dated April 8, 2004. Thereafter, bleed the blue
hydraulic circuit as specified in the AOT within 3 days or 20 flight
hours after performing any maintenance that would normally require
bleeding of the blue hydraulic circuit, (as instructed by the
related aircraft maintenance manual (AMM) procedure).
(g) For airplanes on which maintenance has not been performed on
the blue hydraulic
[[Page 41948]]
circuit as of the effective date of this AD: Within 3 days or 20
flight hours after performing any maintenance that would normally
require bleeding of the blue hydraulic circuit (as instructed by the
related AMM procedure), bleed the blue hydraulic circuit by
accomplishing all the actions specified in Airbus AOT A320-29A1112,
Revision 01, dated April 8, 2004.
Replacement of AGCM and Reducer
(h) Within 35 months after the effective date of this AD,
replace the AGCM with a modified and reidentified AGCM; and replace
the reducer with a new reducer if applicable; in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-29-1111,
dated June 29, 2004. Replacing the AGCM, and the reducer if
applicable, ends the actions required by paragraphs (f) and (g) of
this AD.
Note 1: Airbus Service Bulletin A320-29-1111 refers to Hamilton
Sundstrand Service Bulletin ERPS13GCM-29-5, dated June 29, 2004, as
an additional source of service information for modifying and
reidentifying the AGCM.
Alternative Methods of Compliance (AMOCs)
(i) 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.
Related Information
(j) French airworthiness directive F-2004-150, dated September
1, 2004, also addresses the subject of this AD.
Material Incorporated by Reference
(k) You must use All Operators Telex (Airbus) A320-29A1112,
Revision 01, dated April 8, 2004; and Airbus Service Bulletin A320-
29-1111, dated June 29, 2004; as applicable, to perform the actions
that are required by this AD, unless the AD specifies otherwise. The
Director of the Federal Register approves the incorporation by
reference of these documents in accordance with 5 U.S.C. 552(a) and
1 CFR part 51. To get copies of the service information, contact
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
To view the AD docket, go to the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401,
Nassif Building, Washington, DC. To review copies of the service
information, go to 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 July 8, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-14087 Filed 7-20-05; 8:45 am]
BILLING CODE 4910-13-P