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[Federal Register Volume 79, Number 241 (Tuesday, December 16, 2014)]
[Rules and Regulations]
[Pages 74605-74607]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-29228]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0448; Directorate Identifier 2013-NM-055-AD; 
Amendment 39-18048; AD 2014-25-06]
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 all 
Airbus Model A300 series airplanes; 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 
Airbus Model A310 series airplanes. This AD was prompted by a report of 
early ruptures on the levers of the nose landing gear (NLG) sequence 
valve. This AD requires a one-time inspection for damage of the landing 
gear sequence valve levers and pin shearing indicating areas on the NLG 
and the main landing gears (MLGs); and depending on findings, replacing 
the sequence valve and lever, or doing a one-time inspection to detect 
interference between control rods and sequence valves and corrective 
actions if necessary. We are issuing this AD to detect and correct 
interference between a landing gear leg and door, which could result in 
failure of that landing gear to extend and could damage the airplane 
and injure occupants.

DATES: This AD becomes effective January 20, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 20, 
2015.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0448; or in person at the 
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.
    For service information identified in this AD, contact Airbus SAS, 
Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; 
email account.airworth-eas@airbus.com; Internet http://www.airbus.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.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 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 by adding an AD that would apply to all Airbus Model A300 
series airplanes; 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 Airbus Model A310 series 
airplanes. The NPRM published in the Federal Register on July 16, 2014 
(79 FR 41459).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2013-0058, dated March 11, 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; 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 Airbus Model A310 series 
airplanes. The MCAI states:

    Operators have reported five cases of early ruptures on levers 
of the nose landing gear (NLG) sequence valve.
    Analysis showed that these fatigue ruptures were due to an 
incorrect adjustment of the mechanical links. As the design of the 
main landing gear (MLG) sequence valve lever is similar, there is 
sufficient reason to assume that these parts are similarly affected 
by fatigue.
    This condition, if not detected and corrected, could lead to 
interference between landing gear leg and door and consequent 
failure of the landing gear to extend, possibly resulting in damage 
to the aeroplane and injury to occupants.
    For the reasons described above, this [EASA] AD requires a one-
time inspection of the sequence valve control lever [for damage, 
which could include cracking or deformation], of the adjustment of 
the control rod between doors and landing gear sequence valve and 
depending on inspections results, accomplishment of applicable 
corrective actions.

[[Page 74606]]

    The corrective actions include adjusting the control rod between 
the door and the sequence valves; adjusting mechanical linkages; and 
replacing/installing a serviceable valve and lever. You may examine the 
MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0448-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (79 FR 41459, July 16, 
2014) or on the determination of the cost to the public.

Conclusion

    We reviewed the relevant data 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 (79 FR 41459, July 16, 2014) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 41459, July 16, 2014).

Costs of Compliance

    We estimate that this AD affects 128 airplanes of U.S. registry.
    We also estimate that it would take about 4 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 on U.S. operators to be $43,520, or $340 per product.
    In addition, we estimate that any necessary follow-on actions would 
take up to 9 work-hours and require parts costing up to $42,000, for a 
cost of $42,765 per product. We have no way of determining the number 
of aircraft that might 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 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0448; 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 Operations office (telephone 800-647-
5527) is in the ADDRESSES section.

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):

2014-25-06 Airbus: Amendment 39-18048. Docket No. FAA-2014-0448; 
Directorate Identifier 2013-NM-055-AD.

(a) Effective Date

    This AD becomes effective January 20, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category.
    (1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and 
B4-203 airplanes.
    (2) Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, 
F4-605R, F4-622R, and C4-605R Variant F airplanes.
    (3) Model A310-203, -204, -221, -222, -304, -322, -324, and -325 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear.

(e) Reason

    This AD was prompted by a report of early ruptures on the levers 
of the nose landing gear (NLG) sequence valve. We are issuing this 
AD to detect and correct interference between a landing gear leg and 
door, which could result in failure of that landing gear to extend, 
and could damage the airplane and injure occupants.

(f) Compliance

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

(g) Service Information

    Do the actions required by paragraph (h) of this AD in 
accordance with the applicable service information identified in 
paragraphs (g)(1) through (g)(3) of this AD.
    (1) For Model A300 airplanes: Airbus Service Bulletin A300-32-
0464, dated July 17, 2012.
    (2) For Model A300-600 airplanes: Airbus Service Bulletin A300-
32-6110, dated July 17, 2012.
    (3) For Model A310 airplanes: Airbus Service Bulletin A310-32-
2146, dated July 17, 2012.

(h) Inspections and Corrective Actions

    Within 4,000 flight cycles, 6,000 flight hours, or 30 months 
after the effective date of this AD, whichever occurs first: Do a 
detailed inspection of each sequence valve lever and pin shearing 
indicating area on the nose landing gear and main landing gears for 
any damage, in accordance with the Accomplishment Instructions of 
the applicable service information identified in paragraphs (g)(1) 
through (g)(3) of this AD. Do the actions required by paragraphs 
(h)(1) and (h)(2) of this AD in accordance with the Accomplishment 
Instructions of the applicable service information identified in 
paragraphs (g)(1) through (g)(3) of this AD.
    (1) If damage is found, before further flight, replace the 
affected sequence valve and its lever with a serviceable sequence 
valve and

[[Page 74607]]

lever. No further action is required by paragraph (h) of this AD for 
that replaced valve and lever.
    (2) If no damage is found, within the compliance time required 
by paragraph (h) of this AD, do a detailed inspection to detect 
interference between the landing gear door control rod and the 
landing gear sequence valve, and do all applicable corrective 
actions. Do all applicable corrective actions before further flight. 
No further action is required by paragraph (h) of this AD.
    (3) For the purposes of this AD, a detailed inspection is: An 
intensive examination of a specific item, installation, or assembly 
to detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at an 
intensity deemed appropriate. Inspection aids such as mirror, 
magnifying lenses, etc., may be necessary. Surface cleaning and 
elaborate procedures may be required.

(i) Parts Installation Limitation

    As of the effective date of this AD, no person may install on 
any airplane a landing gear sequence valve, unless that valve has 
been inspected and corrected, as applicable, in accordance with the 
requirements of paragraph (h) of this AD.

(j) 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, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(k) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA Airworthiness Directive 2013-0058, dated March 11, 2013, or 
related information. This MCAI may be found in the AD docket on the 
Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-
0448-0002.

(l) 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 this AD specifies otherwise.
    (i) Airbus Service Bulletin A300-32-0464, dated July 17, 2012.
    (ii) Airbus Service Bulletin A300-32-6110, dated July 17, 2012.
    (iii) Airbus Service Bulletin A310-32-2146, dated July 17, 2012.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet http://www.airbus.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 December 5, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-29228 Filed 12-15-14; 8:45 am]
BILLING CODE 4910-13-P
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