[Federal Register Volume 77, Number 132 (Tuesday, July 10, 2012)]
[Rules and Regulations]
[Pages 40485-40488]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-15897]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0040; Directorate Identifier 2011-NM-121-AD;
Amendment 39-17108; AD 2012-13-06]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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[[Page 40486]]
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A300 series airplanes; all Model A300 B4-600, B4-600R, and
F4-600R series airplanes, and Model 300 C4-605R Variant F airplanes
(collectively called A300-600 series airplanes). This AD was prompted
by reports of an inoperative fire shut-off valve (FSOV) as a result of
damage due to over-length of the bonding lead. This AD requires a one-
time detailed inspection for length of the FSOV bonding leads and for
contact or chafing of the wires, and corrective actions, if necessary.
We are issuing this AD to detect and correct contact or chafing of
wires and bonding leads which, if not detected could be a source of
sparks in the wing trailing edge, and could lead to an uncontrolled
engine fire.
DATES: This AD becomes effective August 14, 2012.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 14,
2012.
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 February 6, 2012 (77
FR 5728). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
During a scheduled maintenance check, one operator reported
inoperative FSOV [fire shut-off valve]. Investigations showed damage
at wire located between engine 2 Hydraulic FSOV and wing rear spar,
in the zones 575/675, and at bonding lead, located between wing Rib
7A and Rib 8 below Hydraulic Pressure Lines.
Similar inspections on different aeroplanes have shown that one
of the causes of damage, is the contact between bonding lead and the
harness, due to over length of the bonding lead.
As the affected wire is not powered during normal operation, no
defect had been detected. The defect was detected when a test was
performed on the FSOV during maintenance check by the operator.
This condition, in the scope of published FAA SFAR88 and JAA
Internal Policy INT/POL/25/12, is considered to be a potential
source of sparks in the wing trailing edge area and if not detected,
could lead to an uncontrolled engine fire.
For the reasons stated above, this [EASA] AD requires a one-time
[detailed] inspection of the wires [for contact or chafing] located
between LH/RH engines Hydraulic FSOV and wing rear spar in the zones
575/675, and the bonding lead [for length] that is located between
Rib 7A and Rib 8 below Hydraulic Pressure Lines, and corrective
actions [repair wires or replace bonding leads] depending on
findings.
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 have considered the comment received.
Request To Extend the Compliance Time
UPS Airlines requested that we extend the compliance time from 30
to 40 months after the effective date of the AD. The commenter stated
the extension is a better fit within the operator's heavy maintenance
program because the extended compliance time is more conducive to
schedule-required aircraft ground time, labor, and parts acquisition.
The commenter stated that the compliance time is too restrictive.
We do not agree with the commenter's request to extend the
compliance time. In developing the proposed compliance time, we
determined that the compliance time of 4,500 flight hours or 30 months
after the effective date of the AD, whichever occurs first, is
appropriate when considering the safety implications, the average
utilization rate of the affected fleet, the practical aspects of an
orderly inspection of the fleet during heavy maintenance checks, and
the availability of required replacement parts. In addition, our
compliance time corresponds with the compliance time of the parallel AD
issued by European Aviation Safety Agency (EASA). We have not changed
the AD in this regard.
Explanation of Change to AD
We have changed paragraph (i) of this AD to include a compliance
time of ``before further flight'' for the wire repair. This compliance
time was required by EASA AD 2011-0084, dated May 24, 2011, and was
inadvertently omitted from the NPRM (77 FR 5728, February 6, 2012).
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 change described previously--and minor editorial changes.
We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (77 FR 5728, February 6, 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 5728, February 6, 2012).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect 125 products of U.S. registry.
We also estimate that it will take about 8 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this AD to the U.S. operators to be $85,000, or $680 per product.
In addition, we estimate that any necessary follow-on actions would
take about 1 work-hour and require parts costing $50, for a cost of
$135 per product. We have no way of determining the number of products
that may need these actions.
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
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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 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 5728, February 6,
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:
2012-13-06 Airbus: Amendment 39-17108. Docket No. FAA-2012-0040;
Directorate Identifier 2011-NM-121-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective August 14,
2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to airplanes specified in paragraphs (c)(1),
(c)(2) and (c)(3) of this AD; certificated in any category; all
certificated models; all serial numbers.
(1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
(2) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R,
B4-622R, F4-605R, and F4-622 airplanes.
(3) Airbus Model A300 C4-605R Variant F airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 24: Electrical
Power.
(e) Reason
This AD was prompted by reports of an inoperative fire shut-off
valve (FSOV) as a result of damage due to over-length of the bonding
lead. We are issuing this AD to detect and correct contact or
chafing of wires and bonding leads which, if not detected, could be
a source of sparks in the wing trailing edge, and could lead to an
uncontrolled engine fire.
(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) Inspection of the FSOV Bonding Leads
Within 4,500 flight hours or 30 months after the effective date
of this AD, whichever occurs first: Do a one-time detailed
inspection for length of the FSOV bonding leads, and for contact or
chafing of the wires located on left hand (LH) side and right-hand
(RH) side of the wing rear spar, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A300-24-0106, dated July 9, 2010 (for Model A300 series airplanes);
or Airbus Mandatory Service Bulletin A300-24-6108, dated July 9,
2010 (for Model A300-600 series airplanes).
(h) Corrective Action for FSOV Bonding Leads
If, during the inspection required by paragraph (g) of this AD,
the length of the bonding lead(s) is more than 80 mm (3.15 inches),
before further flight, replace the bonding lead(s) with a new
bonding lead having a length equal to 80 mm (3.15 inches), in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A300-24-0106, dated July 9, 2010 (for Model A300
series airplanes); or Airbus Mandatory Service Bulletin A300-24-
6108, dated July 9, 2010 (for Model A300-600 series airplanes).
(i) Repair of the Wires of the LH and RH Sides
If, during the inspection required by paragraph (g) of this AD,
contact(s) or chafing(s) of the wires is found, repair the wires,
before further flight, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A300-24-0106,
dated July 9, 2010 (for Model A300 series airplanes); or Airbus
Mandatory Service Bulletin A300-24-6108, dated July 9, 2010 (for
Model A300-600 series airplanes).
(j) Parts Installation Prohibition
As of the effective date of this AD, no person may install any
bonding lead longer than 80 mm (3.15 inches), located between LH/RH
engine hydraulic FSOV and wing rear spar in the zones 575/675 on any
airplane.
(k) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, 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.
(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.
(l) Related Information
Refer to MCAI European Aviation Safety Agency (EASA)
Airworthiness Directive 2011-0084, dated May 24, 2011, and the
service information identified in paragraphs (l)(1) and (l)(2) of
this AD, for related information.
(1) Airbus Mandatory Service Bulletin A300-24-0106, dated July
9, 2010.
(2) Airbus Mandatory Service Bulletin A300-24-6108, dated July
9, 2010.
(m) Material Incorporated by Reference
(1) 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.
(2) You must use the following service information to do the
actions required by this AD, unless the AD specifies otherwise.
(i) Airbus Mandatory Service Bulletin A300-24-0106, excluding
Appendix 01, and including Appendix 2, dated July 9, 2010.
(ii) Airbus Mandatory Service Bulletin A300-24-6108, excluding
Appendix 01 and including Appendix 2, dated July 9, 2010.
(3) For 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) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the
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availability of this material at the FAA, call 425-227-1221.
(5) 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 June 21, 2012.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-15897 Filed 7-9-12; 8:45 am]
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