[Federal Register Volume 81, Number 71 (Wednesday, April 13, 2016)]
[Rules and Regulations]
[Pages 21732-21735]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-08352]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4204; Directorate Identifier 2015-NM-001-AD; 
Amendment 39-18482; AD 2016-08-06]
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 adopting a new airworthiness directive (AD) for certain 
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), modified by a particular supplemental type 
certificate (STC). This AD was prompted by a report of chafing found on 
the overflow sensor harness of the surge tank, and subsequent contact 
between the electrical wiring and fuel tank structure. This AD requires 
a one-time inspection for damage of the outer tank overflow sensor 
harness, and repair if necessary. This AD also requires modification of 
the sensor harness. We are issuing this AD to prevent chafing of the 
harness and subsequent contact between the electrical wiring and fuel 
tank structure, which could result in electrical arcing and a fuel tank 
explosion.

DATES: This AD becomes effective May 18, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of May 18, 2016.

ADDRESSES: For service information identified in this final rule, 
contact Simmonds Precision Products, Inc., A UTC Aerospace Company, 100 
Panton Road, Vergennes, VT 05491; phone 802-877-2911; fax 802-877-4444; 
Internet http://www.utcaerospacesystems.com. You may view this 
referenced 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. It is also 
available on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2015-4204.

[[Page 21733]]

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4204; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (telephone 
800-647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Marc Ronell, Aerospace Engineer, 
Boston Aircraft Certification Office, ANE-150, FAA, 1200 District 
Avenue, Burlington, MA 01803; phone: 781-238-7776; fax: 781-238-7170; 
email: [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain 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), modified by a particular STC. The NPRM published in the 
Federal Register on October 23, 2015 (80 FR 64371) (``the NPRM'').
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0193, dated August 23, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A300 
series airplanes and all Model A300-600 series airplanes.
    The MCAI corresponds to FAA AD 2015-03-03, Amendment 39-18099 (80 
FR 11101, March 2, 2015) (``AD 2015-03-03''), which applies to Airbus 
Model A300 series airplanes and Model A300-600 series airplanes, all 
serial numbers, except for airplanes modified by STC ST00092BO (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/D41C5AE8E46B4901862574900069E004?OpenDocument&Highlight=st00092bo).
    In AD 2015-03-03, we explained that airplanes that have had the in-
tank fuel quantity system modified by STC ST00092BO cannot accomplish 
the actions required by AD 2015-03-03 by using Airbus Service Bulletin 
A300-28-6109, Revision 01, dated December 20, 2013.
    We also stated that we were considering separate rulemaking to 
require the procedures and compliance time specified in UTC Aerospace 
Systems Service Bulletin 300723-28-03 (V-1577), dated October 10, 2014, 
for airplanes modified by STC ST00092BO. We have determined that 
further rulemaking is indeed necessary, and this AD follows from that 
determination.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4204.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comments received. The following 
presents the comments received on the NPRM and the FAA's response to 
each comment.

Request To Extend Proposed Compliance Time

    FedEx asked that we extend the compliance time required by 
paragraph (g) of the proposed AD from 12 to 30 months. FedEx stated 
that AD 2015-03-03 required accomplishing the inspection and rerouting 
within 30 months. FedEx added that, in both AD 2015-03-03 and the NPRM, 
improper harness routing is the root cause of the issue, and stated 
that airplanes having STC ST00092BO have equal susceptibility to 
harness chafing damage as those identified in AD 2015-03-03. FedEx 
suggested that a 30-month compliance time would still provide an 
acceptable level of safety. FedEx added that it is expecting to wait 
four to six months for one of the required materials, and the 
availability of its installation tool has not been confirmed. FedEx 
also stated that a longer compliance time would allow it to minimize 
the operational impact and accomplish the potentially lengthy service 
information at C-checks.
    We do not agree with the commenter's request to extend the 
compliance time, because the request is not supported by any analysis 
or supporting data. This compliance time is shorter to account for the 
time already elapsed for airplanes having STC ST00092BO. In developing 
an appropriate compliance time for the actions specified in this AD, we 
considered the safety implications and normal maintenance schedules for 
the timely accomplishment of the specified actions. We have determined 
that the proposed 12-month compliance time will ensure an acceptable 
level of safety and allow the actions to be done during scheduled 
maintenance intervals for most affected operators. However, affected 
operators may request an alternative method of compliance (AMOC) to 
request an extension of the compliance time under the provisions of 
paragraph (i) of this AD by submitting data and analysis substantiating 
that the change would provide an acceptable level of safety. We have 
not changed this AD in this regard.

Request To Increase Work Hour Estimate

    FedEx stated that, although the referenced service information 
specifies 14 work-hours per airplane for accomplishing both actions, 
the number of work-hours could be closer to 24, especially if a harness 
is replaced.
    We infer that the commenter is requesting that the work-hour 
estimate specified in the ``Costs of Compliance'' section be increased. 
We partially agree with the request. We provided our best estimate for 
the work hours based on the information received from the airplane 
manufacturer and specified in the referenced service information. 
However, we do not know the number of work-hours it would take to 
replace a harness, and as stated in the ``Costs of Compliance'' 
section, we have received no definitive data that would enable us to 
provide cost estimates for the on-condition actions. We have not 
changed this final rule in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this 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 for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    UTC Aerospace Systems has issued Service Bulletin 300723-28-03 (V-
1577), Revision 01, dated July 20, 2015. The service information 
describes procedures for an inspection for damage of the outer tank of 
the overflow sensor harness, repair, and modification of the sensor 
harness. This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business

[[Page 21734]]

or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 65 airplanes of U.S. registry.
    We also estimate that it takes about 3 work-hours per product to 
comply with the inspection required by this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this inspection required by this AD on U.S. operators to be $16,575, or 
$255 per product.
    We estimate that it takes about 11 work-hours per product to comply 
with the modification requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts cost about $100 per product. Based 
on these figures, we estimate the cost of this modification on U.S. 
operators to be $67,275, or $1,035 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

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:
    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.

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 airworthiness 
directive (AD):

2016-08-06 Airbus: Amendment 39-18482; Docket No. FAA-2015-4204; 
Directorate Identifier 2015-NM-001-AD.

(a) Effective Date

    This AD becomes effective May 18, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes specified in paragraphs 
(c)(1), (c)(2), (c)(3), and (c)(4) of this AD; certificated in any 
category; modified by Simmonds Precision Products, Inc., 
Supplemental Type Certificate (STC) ST00092BO (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/D41C5AE8E46B4901862574900069E004?OpenDocument&Highlight=st00092bo).
    (1) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
    (2) Model A300 B4-605R and B4-622R airplanes.
    (3) Model A300 F4-605R and F4-622R airplanes.
    (4) Model A300 C4-605R Variant F airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 28, Fuel.

(e) Reason

    This AD was prompted by a report of chafing found on the 
overflow sensor harness of the surge tank, and subsequent contact 
between the electrical wiring and fuel tank structure. We are 
issuing this AD to prevent chafing of the harness and subsequent 
contact between the electrical wiring and fuel tank structure, which 
could result in electrical arcing and a fuel tank explosion.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) One-Time Inspection and Repair

    Within 12 months after the effective date of this AD: Do the 
actions required by paragraphs (g)(1), (g)(2), and (g)(3) of this 
AD, in accordance with the Accomplishment Instructions of UTC 
Aerospace Systems Service Bulletin 300723-28-03 (V-1577), Revision 
01, dated July 20, 2015.
    (1) Perform a one-time general visual inspection for damage of 
the outer tank sensor harness, and if any damage is found on the 
expando sleeving, before further flight, do a detailed inspection of 
the underlying wires for exposed conductor wires. If any exposed 
conductor wire is found, before further flight, replace the outer 
wing harness assembly.
    (2) Install new brackets and re-route the surge tank overflow 
sensor harness.
    (3) Modify the harness protection.

(h) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(g) of this AD, if those actions were performed before the effective 
date of this AD using UTC Aerospace Systems Service Bulletin 300723-
28-03 (V-1577), dated October 10, 2014. This service information is 
not incorporated by reference in this AD.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Boston Aircraft Certification Office (ACO), 
ANE-150, 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 manager of the ACO, send it to the 
attention of the person identified in paragraph (j)(1) of this AD.
    (2) 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.

(j) Related Information

    (1) For more information about this AD, contact Marc Ronell, 
Aerospace Engineer, Boston Aircraft Certification Office, ANE-150, 
FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-
7776; fax: 781-238-7170; email: [email protected].
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (k)(3) and (k)(4) of this AD.

(k) 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.

[[Page 21735]]

    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) UTC Aerospace Systems Service Bulletin 300723-28-03 (V-
1577), Revision 01, dated July 20, 2015.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Simmonds Precision Products, Inc., A UTC Aerospace Company, 100 
Panton Road, Vergennes, VT 05491; phone 802-877-2911; fax 802-877-
4444; Internet http://www.utcaerospacesystems.com.
    (4) You may view this 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.
    (5) 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 March 30, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-08352 Filed 4-12-16; 8:45 am]
 BILLING CODE 4910-13-P