[Federal Register Volume 78, Number 49 (Wednesday, March 13, 2013)]
[Rules and Regulations]
[Pages 15874-15876]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-04628]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1224; Directorate Identifier 2012-NM-112-AD;
Amendment 39-17372; AD 2013-04-14]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and
Model A300 C4-605R Variant F airplanes (collectively called Model A300-
600 series airplanes); and Model A310 series airplanes. This AD was
prompted by a report of an uncommanded slide back of the co-pilot seat
to the end stop position. This AD requires a one-time inspection for a
part number, a tensile test of the affected seats, and corrective
actions if necessary. We are issuing this AD to detect and prevent
unwanted movement of a pilot or co-pilot seat in the horizontal
direction, which could lead to inadvertent input on the flight control
commands and possibly result in loss of controllability of the
airplane.
DATES: This AD becomes effective April 17, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 17,
2013.
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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-2125; 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 December 10, 2012
(77 FR 73343). That NPRM proposed to correct an unsafe condition for
the specified products. The Mandatory Continuing Airworthiness
Information (MCAI) states:
During a steep climb manoeuvre that was flown with a high pitch
(25[deg]) for training of ground threat avoidance, an Airbus A310
aeroplane experienced an uncommanded slide back of the co-pilot seat
to the end stop position.
Investigation revealed that on the affected seat, the disc key
inside the clutch was broken. SOGERMA Service Bulletin (SB) No
2510112-25-813, which addresses the previous end stop switch issue
and which is covered by [European Aviation Safety Agency] EASA AD
2010-0070 [which corresponds to FAA AD 2011-06-09, Amendment 39-
16634 (76 FR 15805, March 22, 2011)] had been accomplished on this
seat, but due to seizure, the key failure was not detected at time.
This broken disc key caused a jamming between the gear and the shaft
of the clutch. Despite this failure, the torque transmission between
the gear and the shaft was sufficient for normal operation, but not
to keep the seat in locked position during climbing, due to the high
longitudinal loads generated by the high aeroplane incidence.
This condition, if not detected and corrected, could cause the
pilot to lose contact with the controls, leading to an inadvertent
input on the flight control commands during take-off or climb,
possibly resulting in loss of control of the aeroplane.
For the reasons described above, this [EASA] AD requires a one-
time inspection [part number (P/N) inspection of the seats and
tensile test] of the affected seats and, depending on findings,
accomplishment of applicable corrective action(s) [replacing the
seat or modifying the seat by replacing actuator P/N RT19H4FX with a
new actuator].
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 received no comments on the NPRM (77 FR 73343, December 10,
2012), or on the determination of the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed except for
minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (77 FR 73343, December 10, 2012) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 73343, December 10, 2012).
Costs of Compliance
We estimate that this AD will affect 161 products of U.S. registry.
We also estimate that it will take about 1 work-hour per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Required parts will cost about $4,523 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, we estimate the cost of this AD to the
U.S. operators to be $741,888, or $4,608 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 that this AD:
[[Page 15875]]
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 (77 FR 73343, December 10,
2012), 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 adding the following new AD:
2013-04-14 Airbus: Amendment 39-17372. Docket No. FAA-2012-1224;
Directorate Identifier 2012-NM-112-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective April 17,
2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, B4-
622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F
airplanes; and Model A310-203, -204, -221, -222, -304, -322, -324,
and -325 airplanes; certificated in any category; all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 25, Equipment/
Furnishings.
(e) Reason
This AD was prompted by a report of an uncommanded slide back of
the co-pilot seat to the end stop position. We are issuing this AD
to detect and prevent unwanted movement of a pilot or co-pilot seat
in the horizontal direction, which could lead to inadvertent input
on the flight control commands possibly resulting in loss of
controllability of the airplane.
(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) Part Number (P/N) Inspection
Within 6 months after the effective date of this AD, except as
provided by paragraph (h) of this AD: Do an inspection to determine
the part number of each SOGERMA pilot and co-pilot seat installed on
the airplane. As an alternative, a review of the maintenance or
delivery records may be used to determine the part number of the
pilot and co-pilot seat if the part number can be positively
determined from that review.
(h) Seats That Have Been Previously Tested or Modified
SOGERMA pilot and co-pilot seats having P/N 2510112 series (all
suffixes) or P/N 2510113 series (all suffixes) that, before the
effective date of this AD, have already passed the tensile test
specified in paragraph (i) of this AD, or have been modified as
specified in the Operating Instructions of EADS SOGERMA Inspection
Service Bulletin 2510112-25-898, dated April 25, 2012, are not
required to be tested, and are considered to be compliant with the
requirements of this AD.
(i) Tensile Test
If, during the inspection required by paragraph (g) of this AD,
the part number of a seat is identified as P/N 2510112 series (all
suffixes), or P/N 2510113 series (all suffixes): Within 6 months
after the effective date of this AD, do a tensile test on that seat,
in accordance with Airbus Alert Operators Transmission (AOT)
A25W001-12, dated June 6, 2012.
(j) Replacement or Modification
If the tensile test sample does not break off while performing
the test required by paragraph (i) of this AD, before further
flight, do one of the actions specified in paragraph (j)(1) or
(j)(2) of this AD.
(1) Replace the affected seat with a new or serviceable seat
that has passed the tensile test specified in paragraph (i) of this
AD. Do the replacement in accordance with Airbus AOT A25W001-12,
dated June 6, 2012.
(2) Modify the seat by replacing actuator P/N RT19H4FX of the
affected seat, in accordance with the Operating Instructions of EADS
SOGERMA Inspection Service Bulletin 2510112-25-898, dated April 25,
2012; or Airbus AOT A25W001-12, dated June 6, 2012.
(k) Parts Installation Limitations
As of the effective date of this AD, no person may install a
SOGERMA pilot or co-pilot seat having P/N 2510112 series, or P/N
2510113 series, on any airplane unless it has passed the tensile
test required by paragraph (i) of this AD, or has been replaced or
modified as required by paragraph (j) of this AD.
(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: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington
98057-3356; telephone (425) 227-2125; 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 Mandatory Continuing Airworthiness Information European
Aviation Safety Agency Airworthiness Directive 2012-0102, dated June
8, 2012, and the service information specified in paragraphs (m)(1)
and (m)(2) of this AD, for related information.
(1) Airbus Alert Operators Transmission A25W001-12, dated June
6, 2012.
(2) EADS SOGERMA Inspection Service Bulletin 2510112-25-898,
dated April 25, 2012.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Airbus Alert Operators Transmission A25W001-12, dated June
6, 2012.
[[Page 15876]]
(ii) EADS SOGERMA Inspection Service Bulletin 2510112-25-898,
dated April 25, 2012.
(3) For Airbus service information identified in this AD,
contact Airbus SAS -EAW (Airworthiness Office), 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.
(4) For EADS SOGERMA service information identified in this AD,
contact EADS SOGERMA, Zone Industrielle de l'Arsenal, CS. 60109,
17303 Rochefort, Cedex France; phone: 33 5 46 82 84 84; fax: 33 5 46
82 88 13; email: [email protected]; Internet: http://www.sogerma.eads.net.
(5) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA,
call 425-227-1221.
(6) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on February 21, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-04628 Filed 3-12-13; 8:45 am]
BILLING CODE 4910-13-P