Discussion
On September 25, 2012, at 77 FR 58973, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 to include an AD that would apply to Eurocopter Model AS332C, AS332L, and AS332L1 helicopters not modified per modification (MOD) 0723817, MOD 0725670, MOD 332P083218 or MOD 332A088381, with a control panel 33G, part number 332A67-1623-00, -06, -0610, or -0651. That NPRM proposed to require modifying the control panel 33G, connector 100G, and wiring. It also proposed to require tests to ensure that these modifications function correctly. The proposed requirements were intended to prevent an uncommanded landing gear retraction that would cause the helicopter nose to drop and hit the ground while the rotor blades are spinning.
The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD No. 2006-0152, dated May 30, 2006, to correct an unsafe condition for Eurocopter Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. EASA advises of electro-valve power supply disruptions, which caused the landing gear to retract and the helicopter to drop, resulting in damage to the forward section of the helicopter's bottom structure. AD 2006- 0152 requires compliance with Eurocopter Alert Service Bulletin (ASB) No. 32.00.18, Revision 1, dated March 27, 2006, or later revisions and supersedes Direction Generale de L'Aviation Civile France AD No. F- 2005-100, dated June 22, 2005.
Comments
We gave the public the opportunity to participate in developing this AD, but we received no comments on the NPRM (77 FR 58973, September 25, 2012).
FAA's Determination
These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed.
Differences Between This AD and the EASA AD
This AD differs from the EASA AD as follows:
This AD requires compliance within 90 days, while the EASA AD requires compliance within 3 months. The EASA AD also addresses spare parts, and this AD does not address spare parts.
The EASA AD requires a repeat of the tests for helicopters that have been modified in compliance with AD F-2005-100, and this AD does not.
The EASA AD also applies to the Model AS332C1 helicopter, and this AD does not because this model does not have an FAA-issued type certificate.
[[Page 15278]]
Related Service Information
We reviewed Eurocopter ASB No. 32.00.18, Revision 2, dated July 12, 2010, for Model AS332C, AS332C1, AS332L, and AS332L1 helicopters and military Model AS332B, AS332B1, AS332M, AS332M1, AS332F1 helicopters with the specified control panel 33G. That ASB states that electrical interferences on the solenoid valve power supply line have caused untimely retraction of the main landing gear, causing helicopters to sink, resulting in damage to the front section of the helicopter's bottom structure. The ASB describes procedures for modifying the main landing gear control tab on the control panel 33G, replacing the fixed connector on the control panel 33G, replacing the removable connector on the corresponding wiring, and testing the affected systems to ensure that these modifications function correctly. The ASB states that these actions are intended to prevent untimely power supply to the solenoid valve when the main landing gear control tab is on ``extended'' and to avoid main landing gear retraction. EASA AD 2006-0152 classified portions of the ASB as mandatory.
Costs of Compliance
We estimate that this AD affects three helicopters of U.S. registry. We estimate the following costs to comply with this AD:
We estimate that modification of the control panel, connector, and wiring takes one work hour to complete at $85 per hour, and that parts cost $293. Performing function tests takes about 4.5 hours to complete, for a total labor cost of $383. Thus, we estimate a total cost per helicopter of $761, and a total cost of $2,283 for the fleet.
We do not control warranty coverage. Accordingly, we have included all costs in our cost estimate.
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 helicopters identified in this rulemaking action.
Regulatory Findings
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 DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; 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 an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.