[Federal Register Volume 77, Number 49 (Tuesday, March 13, 2012)]
[Rules and Regulations]
[Pages 14679-14681]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-5859]
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Rules and Regulations
Federal Register
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This section of the FEDERAL REGISTER contains regulatory documents
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Federal Register / Vol. 77, No. 49 / Tuesday, March 13, 2012 / Rules
and Regulations
[[Page 14679]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-1087; Directorate Identifier 2011-NM-032-AD;
Amendment 39-16967; AD 2012-04-11]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are superseding two existing airworthiness directives (AD).
One existing AD is for Airbus Model A319, A320, and A321 series
airplanes without Airbus modification 26017. That AD currently requires
replacing the flight warning computers (FWCs). The other existing AD is
for Airbus Model A320 and A321 series airplanes on which Airbus
modification 24612 or Airbus Service Bulletin A320-31-1080 has not been
accomplished. That existing AD currently requires revising the
limitations section of the airplane flight manual. This new AD requires
replacing both FWC units with certain FWC units. This AD was prompted
by in-service events of thrust lever mismanagement and a manufacturer
analysis on the failure to follow procedure or heed existing cockpit
cues. The analysis of the thrust lever management issue showed two
categories of scenarios that could lead to thrust asymmetry during
landing, with controllability and deceleration consequences. We are
issuing this AD to prevent thrust asymmetry conditions which could
result in loss of control of the airplane during landing.
DATES: This AD becomes effective April 17, 2012.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 17,
2012.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of June 24,
2002 (67 FR 35425, May 20, 2002).
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-2141; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on October 19, 2011 (76
FR 64854), and proposed to supersede AD 97-22-13, Amendment 39-10185
(62 FR 58891, October 31, 1997); and AD 2002-10-06, Amendment 39-12752
(67 FR 35425, May 20, 2002). That NPRM proposed to correct an unsafe
condition for the specified products. The MCAI states:
Following in-service experience, analyses of the failure to
follow procedure or heed existing cockpit cues were conducted to
assess the consequences of mismanagement of thrust levers during
landing.
The investigation results identified the need for improvements
in the identification of throttle mis-positioning and so providing
further opportunity for the flight crew to identify an incorrect
thrust lever configuration and to correct this. For the A320 family
of aeroplanes this being IDLE or REVERSE, which is necessary to
enable ground spoiler (G/S) extension and auto-brake (A/BRK)
functions. In addition, the analysis of the thrust lever management
issue shows two categories of scenarios that could lead to thrust
asymmetry during landing with controllability and deceleration
consequences:
--One thrust lever kept in forward thrust when the other is put in
IDLE or REVERSE. This has been seen in cases of dispatch with one
thrust reverser inoperative; and
--One thrust lever moved in forward position after landing, usually
when bringing the thrust lever back from REVERSE to IDLE.
These thrust asymmetry conditions, if not corrected, could
result in loss of control of the aeroplane during landing.
This [EASA] AD supersedes DGAC France AD 94-211-059(B) R2 and
96-079-079(B) [which corresponds to FAA AD 97-22-13 (62 FR 58891,
October 31, 1997], mandating Aircraft Flight Manual Temporary
Revision reference 9.99.99/20 and the installation of FWC P/N
350E017248685 (H1D2) as terminating action for both ADs.
This [EASA] AD retains the requirements of DGAC France AD 2000-
320-147(B) [which corresponds to FAA AD 2002-10-06 (67 FR 35425, May
20, 2002)], which is also superseded, which required the
installation of FWC P/N 350E017271616 (H1E2).
For the reasons described above, this [EASA] AD requires the
replacement of both FWC units with minimum FWC P/N 350E053020909
(H2F5) units, introducing ``Enhanced RETARD'' logic.
You may obtain further information by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received. The commenter supports the
NPRM (76 FR 64854, October 19, 2011).
Explanation of Changes Made to This AD
We have redesignated paragraph (g) and Note 1 of the NPRM (76 FR
64854, October 19, 2011) to paragraphs (g)(1) and (g)(2) in this AD,
respectively. We have revised certain headings throughout this AD. We
have also revised the wording in paragraphs (g)(2) and (j) of this AD;
this change has not changed the intent of those paragraphs.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting the
AD with the changes described previously and minor editorial changes.
We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (76 FR 64854, October 19, 2011) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (76 FR 64854, October 19, 2011).
[[Page 14680]]
Costs of Compliance
We estimate that this AD will affect about 729 products of U.S.
registry. The actions that are required by AD 2002-10-06, Amendment 39-
12752 (67 FR 35425, May 20, 2002) and retained in this AD take about 7
work-hours per product, at an average labor rate of $85 per work hour.
Required parts would cost about $0 per product. Where the service
information lists required parts costs that are covered under warranty,
we have assumed that there will be no charge for these parts. As we do
not control warranty coverage for affected parties, some parties may
incur costs higher than estimated here. Based on these figures, the
estimated cost of the currently required actions is $595 per product.
We estimate that it would take about 4 work-hours per product to
comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts would cost about $0 per
product. Based on these figures, we estimate the cost of this AD on
U.S. operators to be $247,860, or $340 per product.
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 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 this AD:
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);
3. Will not affect intrastate aviation in Alaska; and
4. 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.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM (76 FR 64857, October 19,
2011), the regulatory evaluation, any comments received, and other
information. The street address for the Docket Operations office
(telephone (800) 647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
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 removing AD 97-22-13, Amendment 39-
10185 (62 FR 58891, October 31, 1997); and AD 2002-10-06, Amendment 39-
12752 (67 FR 35425, May 20, 2002); and adding the following new AD:
2012-04-11 Airbus: Amendment 39-16967. Docket No. FAA-2011-1087;
Directorate Identifier 2011-NM-032-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective April 17,
2012.
(b) Affected ADs
This AD supersedes AD 97-22-13, Amendment 39-10185 (62 FR 58891,
October 31, 1997); and AD 2002-10-06, Amendment 39-12752 (67 FR
35425, May 20, 2002).
(c) Applicability
This AD applies to Airbus Model A318-111, -112, -121, and -122
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -
133 airplanes; Model A320-111, -211, -212, -214, -231, -232, and -
233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -
231, and -232 airplanes; certificated in any category; all serial
numbers; if equipped with a flight warning computer (FWC) with a
part number (P/N) listed in table 1 of this AD.
Table 1--List of FWC Part Numbers Affected by This AD
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FWC Part No.
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350E017238484 (H1D1)
350E016187171 (C5)
350E017248685 (H1D2)
350E017251414 (H1E1)
350E017271616 (H1E2)
350E018291818 (H1E3CJ)
350E018301919 (H1E3P)
350E018312020 (H1E3Q)
350E053020202 (H2E2)
350E053020303 (H2E3)
350E053020404 (H2E4)
350E053020606 (H2F2)
350E053020707 (H2F3)
350E053021010 (H2F3P)
350E053020808 (H2F4)
------------------------------------------------------------------------
(d) Subject
Air Transport Association (ATA) of America Code 31: Indicating
and Recording Systems.
(e) Reason
This AD was prompted by in-service events of thrust lever
mismanagement and a manufacturer analysis on the failure to follow
procedure or heed existing cockpit cues. The analysis of the thrust
lever management issue showed two categories of scenarios that could
lead to thrust asymmetry during landing, with controllability and
deceleration consequences. We are issuing this AD to prevent thrust
asymmetry conditions which could result in loss of control of the
airplane during landing.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Restatement of Requirements of AD 2002-10-06, Amendment 39-12752
(67 FR 35425, May 20, 2002): Modification
(1) For Model A319, A320, and A321 series airplanes without
Airbus modification 26017: Within 18 months after June 24, 2002 (the
effective date of AD 2002-10-06, Amendment 39-12752 (67 FR 35425,
May 20, 2002)), replace the flight warning computers (FWCs) in
accordance with Airbus Service Bulletin A320-31-1106, Revision 04,
dated December 21, 1999; or Airbus Mandatory Service Bulletin A320-
31-1106, Revision 05, dated September 21, 2000.
(2) This paragraph provides credit for replacement of the FWCs
required by
[[Page 14681]]
paragraph (g)(1) of this AD, if the replacement was done before June
24, 2002 (the effective date of AD 2002-10-06, Amendment 39-12752
(67 FR 35425, May 20, 2002)), using Airbus Service Bulletin A320-31-
1106, dated January 3, 1997; Revision 01, dated April 16, 1997;
Revision 02, dated January 20, 1998; or Revision 03, dated July 9,
1999.
(h) Restatement of Requirements of AD 2002-10-06, Amendment 39-12752
(67 FR 35425, May 20, 2002): Optional Method of Compliance
Installation of a FWC standard in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-31-1141,
Revision 04, dated February 14, 2002, is an acceptable method of
compliance with the replacement required by paragraph (g) of this
AD.
(i) New Requirements of This AD: Flight Warning Computer Replacement
Within 48 months after the effective date of this AD: Replace
both FWC units with FWC part number 350E053020909, in accordance
with the Accomplishment Instructions of Airbus Mandatory Service
Bulletin A320-31-1334, Revision 04, including Appendix 01, dated
September 12, 2011.
(j) Credit for Previous Actions
(1) For all airplanes, except for Model A319 series airplanes on
which modifications 28238, 28162, and 28342 have been incorporated:
This paragraph provides credit for replacing both FWCs, as required
by paragraph (i) of this AD, if the replacements were performed
before the effective date of this AD using Airbus Service Bulletin
A320-31-1334, dated July 30, 2009; Revision 01, dated December 14,
2009; Revision 02, dated September 13, 2010; or Revision 03, dated
March 15, 2011.
(2) This paragraph provides credit for replacing both FWCs in
lieu of the installation specified in paragraph (h) of this AD, if
the replacements were performed before the effective date of this AD
using Airbus Service Bulletin A320-31-1141, dated March 6, 2000;
Revision 01, dated May 25, 2000; Revision 02, dated January 22,
2001; or Revision 03, dated June 12, 2001.
(k) Parts Installation
As of the effective date of this AD, and after accomplishing the
actions in paragraph (i) of this AD, no person may install a FWC
with a part number listed in table 1 of this AD on any airplane.
(l) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Tim Dulin,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington
98057-3356; telephone 425-227-2141; fax 425-227-1149. Information
may be emailed to: [email protected]. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(m) Related Information
Refer to MCAI EASA Airworthiness Directive 2011-0001, dated
January 10, 2011; Airbus Service Bulletin A320-31-1106, Revision 04,
dated December 21, 1999; Airbus Mandatory Service Bulletin A320-31-
1106, Revision 05, dated September 21, 2000; Airbus Service Bulletin
A320-31-1141, Revision 04, dated February 14, 2002; and Airbus
Mandatory Service Bulletin A320-31-1334, Revision 04, including
Appendix 01, dated September 12, 2011; for related information.
(n) Material Incorporated by Reference
(1) You must use the following service information to do the
actions required by this AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the incorporation by
reference (IBR) of the following service information under 5 U.S.C.
552(a) and 1 CFR part 51 on the date specified.
(2) The following service information was approved for IBR on
April 17, 2012.
(i) Airbus Mandatory Service Bulletin A320-31-1106, Revision 05,
dated September 21, 2000.
(ii) Airbus Service Bulletin A320-31-1141, Revision 04, dated
February 14, 2002.
(iii) Airbus Mandatory Service Bulletin A320-31-1334, Revision
04, including Appendix 01, dated September 12, 2011.
(3) The following service information was approved for IBR on
IBR June 24, 2002 (67 FR 35425, May 20, 2002).
(i) Airbus Service Bulletin A320-31-1106, Revision 04, dated
December 21, 1999.
(4) For service information identified in this AD, contact
Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email: [email protected]; Internet http://www.airbus.com.
(5) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
(6) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at an NARA facility, 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 24, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-5859 Filed 3-12-12; 8:45 am]
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