### 36220 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Proposed Rules

(f) Additional Information

(1) Eurocopter Alert Service Bulletin (ASB) No. AS350–05.00.63, Revision 1, dated April 18, 2011, and ASB No. AS355–05.00.58, Revision 1, dated April 18, 2011, which are not incorporated by reference, contain additional information about the subject of this AD. For this service information, contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, Texas 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http:// www.eurocopter.com/techpub. You may review this service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

(2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2011–0072, dated April 20, 2011.
(g) Subject

Joint Aircraft Service Component (JASC) Code: 2560, Emergency Equipment.

Issued in Fort Worth, Texas, on June 8,
2012. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012–14807 Filed 6–15–12; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0632; Directorate Identifier 2011–SW–044–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Eurocopter France Helicopters** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for all Eurocopter France (Eurocopter) Model SA–365N, SA–365N1, AS–365N2, AS 365 N3, EC 155B, EC155B1, SA–365C, SA–365C1, SA–365C2, and SA–366G1 helicopters. This proposed AD is prompted by reports of corrosion on the main gearbox (MGB) casing lower area between the two servo-control anchoring fitting attachment ribs. An investigation determined that the corrosion was associated with sealing compound on the lower part of the fitting/casing attachment. The proposed actions are intended to detect corrosion on the MGB casing, which could lead to a crack, failure of the MGB, and subsequent loss of control of the helicopter. **DATES :**  We must receive comments on this proposed AD by August 17, 2012.

**ADDRESSES :**  You may send comments by any of the following methods:

• Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically.

• Fax: 202–493–2251.

• Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001.

• Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

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 this proposed AD, the economic 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.

For service information identified in this proposed AD, contact American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 75053–4005, telephone (800) 232–0323, fax (972) 641–3710, or at http:// www.eurocopter.com. You may review a copy of the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

**FOR FURTHER INFORMATION CONTACT :**  Rao Edupuganti, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–4389; email: rao.edupaganti@faa.gov.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time.

We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this proposal in light of the comments we receive.

Discussion

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued AD No.: 2011–0127, dated July 1, 2011 (AD No. 2011–0127), which supersedes Directorate General for Civil Aviation (DGAC France) AD F– 2008–04, dated June 4, 2008, for the Eurocopter Model EC 155 B, EC 155 B1, SA 365 N, SA 365 N1, AS 365 N2, AS 365 N3, SA 366 G1, SA 365 C, SA 365 C1, SA 365 C2, and SA 365 C3 helicopters with a MGB, all part numbers, that was delivered before December 5, 2007, installed on helicopters delivered before December 5, 2007, or overhauled or repaired before September 30, 2008. EASA states that in 2008, it received two reports of atmospheric corrosion on the MGB casing lower area of two helicopters between the two servo-control anchoring fitting attachment ribs. The investigation showed that the corrosion occurred in this area due to the presence of ‘‘PR sealing compound’’ on the lower part of the fitting/casing attachment. The ‘‘PR sealing compound’’ may have been applied incorrectly on some helicopters due to a misinterpretation of the Eurocopter documentation during installation. EASA states that this condition, if not corrected, could lead to ‘‘crack initiation and crack growth in the affected area of the casing,’’ which could cause this area to fail and result in loss of control of the helicopter.

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 its AD. We are proposing this AD because we evaluated all known relevant information and determined that an


### 36221 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Proposed Rules

unsafe condition is likely to exist or develop on other products of these same type designs.

Related Service Information

Eurocopter has issued one Emergency Alert Service Bulletin (EASB), Revision 0, dated May 7, 2008, with five different numbers. EASB No. 63.00.17 is for the Model AS 365-series helicopters; EASB No. 63.00.12 is for the military Model AS 565-series helicopters, which are not FAA type certificated; EASB No. 63A011 is for the Model EC 155-series helicopters; EASB No. 65.03 is for the Model SA 366-series helicopters; and EASB No. 65.47 is for the Model SA 365-series helicopters and the non-FAA type certificated Model SA 360-series helicopters. The EASB specifies inspecting for ‘‘PR sealing compound’’ on the lower parts of the MGB anchoring fittings, removing any ‘‘PR sealing compound,’’ and repairing any corrosion. EASA classified this EASB as mandatory and issued AD No. 2011– 0127 to ensure the continued airworthiness of these helicopters. Proposed AD Requirements

This proposed AD would require the following actions:

• Within 30 hours time-in-service (TIS), inspecting the lower parts of the anchoring fittings for sealing compound.

• If there is sealing compound on the lower parts of the anchoring fittings, removing the sealing compound and inspecting the anchoring fittings for corrosion.

• If there is corrosion, repairing the affected area. If there is no corrosion, applying touch up protective treatment and renewing any damaged sealing compound bead in the lower part of the anchoring fitting. Differences Between This Proposed AD and the EASA AD

The EASA AD requires inspecting the anchoring fittings for ‘‘PR sealing compound’’ within 15 flight hours, while this proposed AD would require inspecting within 30 hours TIS. The EASA AD applies to the Model SA– 365C3, and this proposed AD does not include this model because it does not have an FAA-issued type certificate. This AD would not allow the compliance times provided in Appendix 1 of the EASA AD, since it is desirable to accomplish any required repairs before further flight. Costs of Compliance

We estimate that this proposed AD would affect 31 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. Inspecting the anchor fittings for sealing compound and corrosion will require about .5 work hour at an average labor rate of $85 per hour, for a cost per helicopter of about $43 and a cost to the entire U.S. fleet of $1,318. To remove any sealing compound and repair any corrosion damage will require about 8 work hours at an average labor rate of $85 per hour, for a cost per helicopter of $680. 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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, I certify this proposed regulation:

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 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 proposed 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. The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

**PART 39—AIRWORTHINESS DIRECTIVES** 

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

**§ 39.13 [Amended]**

2. The FAA amends § 39.13 by adding the following new Airworthiness Directive (AD):
Eurocopter France Helicopters: Docket No. FAA–2012–0632; Directorate Identifier 2011–SW–044–AD. (a) Applicability

This AD applies to Eurocopter Model SA– 365N, SA–365N1, AS–365N2, AS 365 N3, EC 155B, EC155B1, SA–366G1, SA–365C, SA– 365C1, and SA–365C2 helicopters, with a main gearbox (MGB) installed, certificated in any category.
(b) Unsafe Condition

This AD defines the unsafe condition as corrosion on the MGB casing lower area between the servo-control anchoring ribs, caused by sealing compound on the lower part of the fitting/casing attachment. This condition could result in a crack, failure of the MGB, and subsequent loss of control of the helicopter.
(c) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(d) Required Actions

(1) Within 30 hours time-in-service,inspect the lower parts of the MGB servocontrol anchoring fittings (anchor fittings) for sealing compound, referring to Figure 1 of Eurocopter Emergency Alert Service Bulletin No. 63.00.17 (for Models SA–365N, SA– 365N1, AS–365N2 and AS 365 N3); No. 63A011 (for Models EC 155B and EC155B1); No. 65.03 (for Model SA–366G1); and No. 65.47 (for Models SA–365C, SA–365C1, and SA–365C2), Revision 0, dated May 7, 2008 (EASB).

Note to (d)(1): The Eurocopter EASB is one document with multiple EASB numbers, each applicable to different base model Eurocopter helicopters.

(2) If there is sealing compound on the lower part of an MGB anchor fitting, remove the sealing compound and inspect for corrosion in the lower area of the MGB casing.

(i) If there is corrosion, before further flight, repair the corrosion area.


### 36222 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Proposed Rules

(ii) If there is no corrosion, apply touch up protective treatment, if required, and renew the bead of any damaged sealing compound in the upper part of the anchor fitting.
(e) Alternative Methods of Compliance (AMOC)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Rao Edupuganti, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–4389; email: rao.edupaganti@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC.

(f) Additional Information

(1) Eurocopter Repair Sheet 365–63–36–08, dated April 4, 2008 and Standard Practices Manual (MTC) Work Cards 20.04.04, 20.04.05, and 20.05.01, which are not incorporated by reference, contain additional information regarding the subject of this proposed AD and in particular regarding the procedures for corrosion repair, protective treatment touch-up, and renewing the damaged sealing bead.

(2) For service information identified in this AD, contact American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 75053–4005, telephone (800) 232–0323, fax (972) 641–3710, or at http:// www.eurocopter.com. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

(3) The subject of this AD is addressed in European Aviation Safety Agency AD No. 2011–0127, dated July 1, 2011.
(g) Subject

Joint Aircraft Service Component (JASC) Code: 6320: Main Rotor Gearbox.

Issued in Fort Worth, Texas, on June 7,

2012. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012–14805 Filed 6–15–12; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0637; Directorate Identifier 2012–NM–006–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737–600, –700, –700C, –800, –900, and –900ER series airplanes. This proposed AD was prompted by a report of an inboard main landing gear (MLG) door assembly departure due to premature fatigue cracking in the inboard MLG door hinge fittings. This proposed AD would require repetitive inspections for cracking of the inboard MLG door hinge fittings; and modification of cracked fittings, which would terminate the repetitive inspections. We are proposing this AD to detect and correct fatigue cracking in the inboard MLG door hinge fittings which could result in loss of the MLG door assembly from the airplane; loss of the MLG door assembly could impact the flight control surfaces and result in reduced controllability of the airplane.

**DATES :**  We must receive comments on this proposed AD by August 2, 2012.

**ADDRESSES :**  You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: 202–493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

• Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–
1221. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the

**ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425– 917–6440; fax: 425–917–6590; email: nancy.marsh@faa.gov.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA– 2012–0637; Directorate Identifier 2012– NM–006–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those
comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

We received a report of an inboard MLG door assembly departure due to premature fatigue cracking in the inboard MLG door hinge fittings. Fatigue cracking in the inboard MLG door hinge fittings could result in loss of the MLG door assembly from the airplane; such loss could impact the flight control surfaces and result in reduced controllability of the airplane.