Airworthiness Directives; Eurocopter France (Eurocopter) Model AS332C, AS332L, AS332L1, and AS332L2 Helicopters, 66606-66609 [2011-27673]

Download as PDF 66606 § 917.143 Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations [Amended] 21. In § 917.143, lift the suspension of April 18, 2011 (76 FR 21618); remove the words ‘‘and peaches’’ from the introductory text of paragraph (b) and from paragraphs (b)(1), (b)(2), and (b)(4); remove the words ‘‘and 200 pounds of peaches’’ from paragraph (b)(3); and suspend the section indefinitely. ■ § 917.150 ■ [Removed] 22. Remove § 917.150. Subpart—Assessment Rates (§§ 917.258 through 917.259) [Removed] 23. Remove Subpart—Assessment Rates, consisting of §§ 917.258 through 917.259. ■ Subpart—Container and Pack Regulation (§§ 917.442) [Removed] 24. Remove Subpart—Container and Pack Regulation, consisting of § 917.442. ■ § 917.459 ■ [Removed] 25. Remove §§ 917.459. Dated: October 14, 2011. David R. Shipman, Acting Administrator, Agricultural Marketing Service. [FR Doc. 2011–27286 Filed 10–26–11; 8:45 am] BILLING CODE 3410–02–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0939; Directorate Identifier 2010–SW–067–AD; Amendment 39 16798; AD 2011–18–16] RIN 2120–AA64 Airworthiness Directives; Eurocopter France (Eurocopter) Model AS332C, AS332L, AS332L1, and AS332L2 Helicopters Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. AGENCY: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter model helicopters. This action requires inspecting the upper end fitting ball joints of the main rotor servocontrols for lateral play, and depending on the findings either repetitively inspecting the ball joint or replacing the servocontrol. This amendment is prompted by reports of noncompliant swaging of the end fitting ball joints on main rotor servocontrols. mstockstill on DSK4VPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 17:05 Oct 26, 2011 Jkt 226001 Investigation has shown that the swaging load applied to the ball joints was 1.3 metric tons instead of the specified 13 metric tons. The actions specified in this AD are intended to prevent failure of the upper end fitting ball joints of the main rotor servocontrols, failure of the upper end fittings, and loss of control of the helicopter. DATES: Effective November 14, 2011. Comments for inclusion in the Rules Docket must be received on or before December 27, 2011. ADDRESSES: Use one of the following addresses to submit comments on this AD: • 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may get the service information identified in this AD from 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. Examining the Docket: You may examine the docket that contains the AD, any comments, and other information 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 Docket Operations office (telephone (800) 647 5527) is located in Room W12–140 on the ground floor of the West Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–5130, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD No. 2010– PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 0117–E, dated June 16, 2010, to correct an unsafe condition for the specified Eurocopter model helicopters. EASA advises that the equipment manufacturer (Goodrich) has identified two servocontrol production batches as noncompliant with swaging of the end fitting ball joints on main rotor servocontrols. EASA states that investigations have revealed that the swaging load applied to the ball joints in these two batches was 1.3 metric tons, instead of the specified 13 metric tons, which could lead the ball joints to slip in service. The slipping of the ball joint of the servocontrol lower end fitting does not significantly affect the service life of the end fitting. However, the slipping of the ball joint of the servocontrol upper end fitting can lead to a significant reduction in the service life of the end fitting. This condition, if not corrected, could lead to failure of the upper end fitting ball joint of a main rotor servocontrol and result in loss of control of the helicopter. Differences Between This AD and the EASA AD We refer to flight hours as hours timein-service (TIS). Related Service Information Eurocopter has issued an Emergency Alert Service Bulletin (EASB), dated June 15, 2010, with two numbers: No. 67.00.40 for FAA type-certificated Models AS332C, L, L1, and L2 and for Models AS332C1, B, B1, F1, M, and M1 that are not FAA type certificated, and No. 67.00.27 for Models AS532AC, AL, SC, UC, UE, UL, A2, and U2 that are not FAA type certificated. The EASB specifies checking and restoring conformity of the affected end fitting ball joints of the servocontrols. The EASB contains Appendix 1 and 2, Goodrich Service Bulletins No. SC7203– 67–31–02 and No. SC7221–67–39–02, both dated May 11, 2010, which specify the process for comforming each affected servocontrol. EASA classified this EASB as mandatory and issued Emergency AD No. 2010–0117–E, dated June 16, 2010, to ensure the continued airworthiness of these helicopters. FAA’s Evaluation and Unsafe Condition 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, their 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 E:\FR\FM\27OCR1.SGM 27OCR1 Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs. Eurocopter states that there are currently no helicopters with the affected part installed in the United States. However, this rule is necessary to ensure that the described unsafe condition is addressed in the event this part is installed on any helicopter in the future. Costs of Compliance There are no costs of compliance assuming that there are no helicopters on the U.S. Registry with the affected part installed as represented by the manufacturer. mstockstill on DSK4VPTVN1PROD with RULES FAA’s Determination of the Effective Date This unsafe condition is likely to exist or develop on other helicopters of these same type designs. Therefore, this AD is being issued to prevent failure of the upper end fitting ball joints of the main rotor servocontrols, failure of the upper end fittings, and loss of control of the helicopter. Since there are currently no U.S. registered helicopters with the affected part installed, we have determined that notice and opportunity for prior public comment before issuing this AD are unnecessary and that good cause exists for making this amendment effective in less than 30 days. Requirements of This AD This AD requires: • Within 15 hours TIS, unless accomplished previously, using a feeler gage, measuring the lateral play between the outer ring of the ball joint and each of the two faces of the upper end fitting. • If the lateral play is greater than or equal to 1 millimeter (MM) (0.04 inch) and the servocontrol has accumulated 825 or more hours TIS, replacing it with an airworthy servocontrol before further flight. • If the lateral play is greater than or equal to 1 mm (0.04 inch) and the servocontrol has accumulated less than 825 hours TIS, on or before the servocontrol accumulates 825 hours TIS, replacing it with an airworthy servocontrol. • If the lateral play is less than 1 mm (0.04 inch), thereafter, at intervals not to exceed 300 hours TIS, repeating the inspection. At each 300-hour TIS inspection, if the lateral play is greater than or equal to 1 mm (0.04 inch), within 525 hours TIS, replacing the servocontrol with an airworthy servocontrol. • Replacing the servocontrol with an airworthy servocontrol that is not included in the AD applicability or that VerDate Mar<15>2010 17:05 Oct 26, 2011 Jkt 226001 is modified with a letter ‘‘R’’ after the S/ N constitutes terminating action for the requirements of this AD. Because these affected parts have an unlimited operational fatigue life with no previous fatigue inspections required, the replacement criteria of this AD assumes that the affected servocontrols found to have greater than or equal to 1 MM of lateral play have already been operated for at least 825 hours TIS with this fatigue damage and must be replaced at 825 hours TIS or if they have already accumulated 825 or more hours TIS, within 15 hours TIS of the effective date of this AD. However, if a subsequent 300-hour TIS repetitive inspection required by this AD reveals lateral play of 1 MM or greater, those affected servocontrols may be operated an additional 525 hours TIS because the previous 300-hours TIS inspection established the new baseline for the 825 hours TIS thereby allowing an additional 525 hours TIS before replacement. Comments Invited This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include FAA Docket No. ‘‘FAA–2011– 0939; Directorate Identifier 2010–SW– 067–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the AD in light 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 with FAA personnel concerning this AD. Using the search function of the docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent the comment. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477 78). Regulatory Findings We have determined that notice and prior public comment are unnecessary in promulgating this regulation; therefore, it can be issued immediately to correct an unsafe condition in aircraft because none of the model helicopters PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 66607 that are registered in the United States have the affected part installed. We have also determined that this regulation is not a ‘‘significant regulatory action’’ under Executive Order 12866. It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If it is determined that this emergency regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the AD docket. 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive (AD) to read as follows: ■ 2011–18–16 Eurocopter France: Amendment 39–16798; Docket No. FAA 2011–0939; Directorate Identifier 2010– SW–067–AD. E:\FR\FM\27OCR1.SGM 27OCR1 66608 Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations 1727, which are not marked with a letter ‘‘R’’ after the S/N, certificated in any category. Compliance: Required as indicated. To prevent failure of the upper end fitting ball joints of the main rotor servocontrols, failure of the upper end fittings, and loss of control of the helicopter, do the following: (a) Within 15 hours time-in-service (TIS), unless accomplished previously, using a feeler gage, measure the lateral play between the outer ring of the ball joint and each of the two faces of the upper end fitting as depicted in Figure 1 of this AD. (b) If the lateral play is greater than or equal to 1 millimeter (MM) (0.04 inch) and the servocontrol has accumulated 825 or more hours TIS, before further flight, replace it with an airworthy servocontrol. (c) If the lateral play is greater than or equal to 1 mm (0.04 inch) and the servocontrol has accumulated less than 825 hours TIS, on or before the servocontrol accumulates 825 hours TIS, replace it with an airworthy servocontrol. (d) If the lateral play is less than 1 mm (0.04 inch), at intervals not to exceed 300 hours TIS, repeat the inspection required by paragraph (a) of this AD. At each 300 hour TIS interval inspection, if the lateral play is greater than or equal to 1 mm (0.04 inch), within 525 hours TIS, replace the servocontrol with an airworthy servocontrol. Note 1: An acceptable method of returning the servocontrol to an airworthy condition VerDate Mar<15>2010 17:05 Oct 26, 2011 Jkt 226001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\27OCR1.SGM 27OCR1 ER27OC11.001</GPH> mstockstill on DSK4VPTVN1PROD with RULES Applicability: Models AS332C, L, L1, and L2 helicopters, with main rotor servocontrols, part number (P/N) SC7203–1 with serial number (S/N) 633 through 643, 645 through 659, 664 or 665, or P/N SC7221– 1 with S/N 1693 through 1723 and 1726 or Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations for the purposes of this AD is by modifying the servocontrol and marking an ‘‘R’’ after the S/N by following Goodrich Service Bulletin (SB) No. SC7203–67–31–02, dated May 11, 2010, for servocontrol, P/N SC7203–1, or Goodrich SB No. SC72216739–02, dated May 11, 2010, for servocontrol, P/N SC7221 1. The Goodrich SBs are attached to Eurocopter Emergency Alert SB containing two numbers (67.00.40 and 67–00.27), dated June 15, 2010 as Appendix 1 and Appendix 2, respectively. None of these three SBs is incorporated by reference in this AD. (e) Replacing a servocontrol with an airworthy servocontrol that is marked with a letter ‘‘R’’ by the manufacturer after the S/N constitutes terminating action for the requirements of this AD. (f) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Safety Management Group, Rotorcraft Directorate, FAA, ATTN: Gary Roach, Aviation Safety Engineer, FAA, Regulations and Guidance Group, 2601 Meacham Blvd, Fort Worth, Texas 76137, telephone (817) 222–5130, fax (817) 222 5961, for information about previously approved alternative methods of compliance. (g) The Joint Aircraft System/Component (JASC) Code is 6730: Rotorcraft Servo System. (h) This amendment becomes effective on November 14, 2011. Note 2: The subject of this AD is addressed in European Aviation Safety Agency Emergency AD No. 2010–0117–E, dated June 16, 2010. Issued in Fort Worth, Texas, on August 23, 2011. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2011–27673 Filed 10–26–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–1035; Directorate Identifier 2011–SW–038–AD; Amendment 39–16817; AD 2011–15–51] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada (Bell) Model 407 and 427 Helicopters Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. mstockstill on DSK4VPTVN1PROD with RULES AGENCY: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2011–15–51, which was sent previously to all known U.S. owners and operators SUMMARY: VerDate Mar<15>2010 17:05 Oct 26, 2011 Jkt 226001 of the specified Bell Model 407 and 427 helicopters by individual letters. This AD requires inspecting certain hydraulic servo actuators to determine whether the shaft turns independently of the nut or the clevis assembly. If the shaft turns independently, this AD requires replacing the servo with an airworthy servo. If the shaft does not turn independently, the AD requires inspecting to determine the condition of the lock washers. Based on the condition of the lock washers, the AD requires either replacing the servo with an airworthy servo, or if any tab of the lock washer is not flush against a flat surface of the nut or clevis assembly, bending it flush against a flat surface. The AD also requires reidentifying the servo by metal-impression stamping or by vibro-etching ‘‘67.01’’ onto the modification plate. Also, the AD requires before installing a servo with a part number or serial number identified in this AD, not identified by ‘‘67–01’’ on the modification plate, inspecting it by following the requirements of this AD. This AD is prompted by a report that a quality escape by a supplier has occurred and certain servos may have a loose nut, shaft, and clevis assembly due to improper lock-washer installation. An investigation after an accident revealed the clevis nut on the servo was loose. The actions specified by this AD are intended to prevent a malfunction of a servo in the flight control system and subsequent loss of control of the helicopter. DATES: Effective November 14, 2011, to all persons except those persons to whom it was made immediately effective by Emergency AD 2011–15–51, issued on July 8, 2011, which contained the requirements of this amendment. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of November 14, 2011. Comments for inclusion in the Rules Docket must be received on or before December 27, 2011. ADDRESSES: Use one of the following addresses to submit comments on this AD: • 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 66609 W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may get the service information identified in this AD from Bell Helicopter Textron Canada Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437–2862 or (800) 363–8023, fax (450) 433–0272, or at http://www.bellcustomer.com/files/. Examining the Docket: You may examine the docket that contains the AD, any comments, and other information 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 Docket Operations office (telephone (800) 647– 5527) is located in Room W12–140 on the ground floor of the West Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Matt Wilbanks, Aviation Safety Engineer, 2601 Meacham Blvd, Fort Worth, Texas 76137, telephone (817) 222–5051, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: On July 8, 2011, the FAA issued Emergency AD 2011–15–51 for the specified model helicopters, which requires inspecting certain servos to determine whether the shaft turns independently of the nut or the clevis assembly. If the shaft turns independently, the AD requires replacing the servo with an airworthy servo. If the shaft does not turn independently, the AD requires inspecting to determine the condition of the lock washers. If at least one lock washer is not bent flush against a flat surface of the nut and at least one tab of the lock washer is not bent flush against a flat surface of the clevis assembly, the AD requires replacing the servo with an airworthy servo. If any tab of the lock washer is not bent flush against either a flat surface of the nut or clevis assembly, the AD requires bending the tab flush against a flat surface. The AD also requires reidentifying the servo by metalimpression stamping or by vibro-etching ‘‘67.01’’ onto the modification plate. Also, the AD requires before installing a servo with a part number or serial number identified in this AD, not identified by ‘‘67–01’’ on the modification plate, inspecting and reidentifying it by following the requirements of this AD. That action was prompted by a report that a quality escape by a supplier has occurred and certain servos may have a loose nut, E:\FR\FM\27OCR1.SGM 27OCR1

Agencies

[Federal Register Volume 76, Number 208 (Thursday, October 27, 2011)]
[Rules and Regulations]
[Pages 66606-66609]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-27673]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0939; Directorate Identifier 2010-SW-067-AD; 
Amendment 39 16798; AD 2011-18-16]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France (Eurocopter) Model 
AS332C, AS332L, AS332L1, and AS332L2 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
the specified Eurocopter model helicopters. This action requires 
inspecting the upper end fitting ball joints of the main rotor 
servocontrols for lateral play, and depending on the findings either 
repetitively inspecting the ball joint or replacing the servocontrol. 
This amendment is prompted by reports of noncompliant swaging of the 
end fitting ball joints on main rotor servocontrols. Investigation has 
shown that the swaging load applied to the ball joints was 1.3 metric 
tons instead of the specified 13 metric tons. The actions specified in 
this AD are intended to prevent failure of the upper end fitting ball 
joints of the main rotor servocontrols, failure of the upper end 
fittings, and loss of control of the helicopter.

DATES: Effective November 14, 2011.
    Comments for inclusion in the Rules Docket must be received on or 
before December 27, 2011.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
     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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    You may get the service information identified in this AD from 
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.
    Examining the Docket: You may examine the docket that contains the 
AD, any comments, and other information 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 Docket Operations office (telephone (800) 647 5527) is 
located in Room W12-140 on the ground floor of the West Building at the 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Regulations and Guidance Group, 2601 
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5130, fax 
(817) 222-5961.

SUPPLEMENTARY INFORMATION: 

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
No. 2010-0117-E, dated June 16, 2010, to correct an unsafe condition 
for the specified Eurocopter model helicopters. EASA advises that the 
equipment manufacturer (Goodrich) has identified two servocontrol 
production batches as noncompliant with swaging of the end fitting ball 
joints on main rotor servocontrols. EASA states that investigations 
have revealed that the swaging load applied to the ball joints in these 
two batches was 1.3 metric tons, instead of the specified 13 metric 
tons, which could lead the ball joints to slip in service. The slipping 
of the ball joint of the servocontrol lower end fitting does not 
significantly affect the service life of the end fitting. However, the 
slipping of the ball joint of the servocontrol upper end fitting can 
lead to a significant reduction in the service life of the end fitting. 
This condition, if not corrected, could lead to failure of the upper 
end fitting ball joint of a main rotor servocontrol and result in loss 
of control of the helicopter.

Differences Between This AD and the EASA AD

    We refer to flight hours as hours time-in-service (TIS).

Related Service Information

    Eurocopter has issued an Emergency Alert Service Bulletin (EASB), 
dated June 15, 2010, with two numbers: No. 67.00.40 for FAA type-
certificated Models AS332C, L, L1, and L2 and for Models AS332C1, B, 
B1, F1, M, and M1 that are not FAA type certificated, and No. 67.00.27 
for Models AS532AC, AL, SC, UC, UE, UL, A2, and U2 that are not FAA 
type certificated. The EASB specifies checking and restoring conformity 
of the affected end fitting ball joints of the servocontrols. The EASB 
contains Appendix 1 and 2, Goodrich Service Bulletins No. SC7203-67-31-
02 and No. SC7221-67-39-02, both dated May 11, 2010, which specify the 
process for comforming each affected servocontrol. EASA classified this 
EASB as mandatory and issued Emergency AD No. 2010-0117-E, dated June 
16, 2010, to ensure the continued airworthiness of these helicopters.

FAA's Evaluation and Unsafe Condition 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, their 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

[[Page 66607]]

unsafe condition exists and is likely to exist or develop on other 
helicopters of these same type designs.
    Eurocopter states that there are currently no helicopters with the 
affected part installed in the United States. However, this rule is 
necessary to ensure that the described unsafe condition is addressed in 
the event this part is installed on any helicopter in the future.

Costs of Compliance

    There are no costs of compliance assuming that there are no 
helicopters on the U.S. Registry with the affected part installed as 
represented by the manufacturer.

FAA's Determination of the Effective Date

    This unsafe condition is likely to exist or develop on other 
helicopters of these same type designs. Therefore, this AD is being 
issued to prevent failure of the upper end fitting ball joints of the 
main rotor servocontrols, failure of the upper end fittings, and loss 
of control of the helicopter. Since there are currently no U.S. 
registered helicopters with the affected part installed, we have 
determined that notice and opportunity for prior public comment before 
issuing this AD are unnecessary and that good cause exists for making 
this amendment effective in less than 30 days.

Requirements of This AD

    This AD requires:
     Within 15 hours TIS, unless accomplished previously, using 
a feeler gage, measuring the lateral play between the outer ring of the 
ball joint and each of the two faces of the upper end fitting.
     If the lateral play is greater than or equal to 1 
millimeter (MM) (0.04 inch) and the servocontrol has accumulated 825 or 
more hours TIS, replacing it with an airworthy servocontrol before 
further flight.
     If the lateral play is greater than or equal to 1 mm (0.04 
inch) and the servocontrol has accumulated less than 825 hours TIS, on 
or before the servocontrol accumulates 825 hours TIS, replacing it with 
an airworthy servocontrol.
     If the lateral play is less than 1 mm (0.04 inch), 
thereafter, at intervals not to exceed 300 hours TIS, repeating the 
inspection. At each 300-hour TIS inspection, if the lateral play is 
greater than or equal to 1 mm (0.04 inch), within 525 hours TIS, 
replacing the servocontrol with an airworthy servocontrol.
     Replacing the servocontrol with an airworthy servocontrol 
that is not included in the AD applicability or that is modified with a 
letter ``R'' after the S/N constitutes terminating action for the 
requirements of this AD.
    Because these affected parts have an unlimited operational fatigue 
life with no previous fatigue inspections required, the replacement 
criteria of this AD assumes that the affected servocontrols found to 
have greater than or equal to 1 MM of lateral play have already been 
operated for at least 825 hours TIS with this fatigue damage and must 
be replaced at 825 hours TIS or if they have already accumulated 825 or 
more hours TIS, within 15 hours TIS of the effective date of this AD. 
However, if a subsequent 300-hour TIS repetitive inspection required by 
this AD reveals lateral play of 1 MM or greater, those affected 
servocontrols may be operated an additional 525 hours TIS because the 
previous 300-hours TIS inspection established the new baseline for the 
825 hours TIS thereby allowing an additional 525 hours TIS before 
replacement.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any written data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include FAA Docket No. ``FAA-2011-0939; 
Directorate Identifier 2010-SW-067-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD. We will consider 
all comments received by the closing date and may amend the AD in light 
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 
with FAA personnel concerning this AD. Using the search function of the 
docket Web site, you can find and read the comments to any of our 
dockets, including the name of the individual who sent the comment. You 
may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477 78).

Regulatory Findings

    We have determined that notice and prior public comment are 
unnecessary in promulgating this regulation; therefore, it can be 
issued immediately to correct an unsafe condition in aircraft because 
none of the model helicopters that are registered in the United States 
have the affected part installed. We have also determined that this 
regulation is not a ``significant regulatory action'' under Executive 
Order 12866. It has been determined further that this action involves 
an emergency regulation under DOT Regulatory Policies and Procedures 
(44 FR 11034, February 26, 1979). If it is determined that this 
emergency regulation otherwise would be significant under DOT 
Regulatory Policies and Procedures, a final regulatory evaluation will 
be prepared and placed in the AD docket.

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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive 
(AD) to read as follows:

    2011-18-16 Eurocopter France: Amendment 39-16798; Docket No. FAA 
2011-0939; Directorate Identifier 2010-SW-067-AD.


[[Page 66608]]


    Applicability: Models AS332C, L, L1, and L2 helicopters, with 
main rotor servocontrols, part number (P/N) SC7203-1 with serial 
number (S/N) 633 through 643, 645 through 659, 664 or 665, or P/N 
SC7221-1 with S/N 1693 through 1723 and 1726 or 1727, which are not 
marked with a letter ``R'' after the S/N, certificated in any 
category.
    Compliance: Required as indicated.
    To prevent failure of the upper end fitting ball joints of the 
main rotor servocontrols, failure of the upper end fittings, and 
loss of control of the helicopter, do the following:
    (a) Within 15 hours time-in-service (TIS), unless accomplished 
previously, using a feeler gage, measure the lateral play between 
the outer ring of the ball joint and each of the two faces of the 
upper end fitting as depicted in Figure 1 of this AD.
[GRAPHIC] [TIFF OMITTED] TR27OC11.001

    (b) If the lateral play is greater than or equal to 1 millimeter 
(MM) (0.04 inch) and the servocontrol has accumulated 825 or more 
hours TIS, before further flight, replace it with an airworthy 
servocontrol.
    (c) If the lateral play is greater than or equal to 1 mm (0.04 
inch) and the servocontrol has accumulated less than 825 hours TIS, 
on or before the servocontrol accumulates 825 hours TIS, replace it 
with an airworthy servocontrol.
    (d) If the lateral play is less than 1 mm (0.04 inch), at 
intervals not to exceed 300 hours TIS, repeat the inspection 
required by paragraph (a) of this AD. At each 300 hour TIS interval 
inspection, if the lateral play is greater than or equal to 1 mm 
(0.04 inch), within 525 hours TIS, replace the servocontrol with an 
airworthy servocontrol.

    Note 1:  An acceptable method of returning the servocontrol to 
an airworthy condition

[[Page 66609]]

for the purposes of this AD is by modifying the servocontrol and 
marking an ``R'' after the S/N by following Goodrich Service 
Bulletin (SB) No. SC7203-67-31-02, dated May 11, 2010, for 
servocontrol, P/N SC7203-1, or Goodrich SB No. SC72216739-02, dated 
May 11, 2010, for servocontrol, P/N SC7221 1. The Goodrich SBs are 
attached to Eurocopter Emergency Alert SB containing two numbers 
(67.00.40 and 67-00.27), dated June 15, 2010 as Appendix 1 and 
Appendix 2, respectively. None of these three SBs is incorporated by 
reference in this AD.

    (e) Replacing a servocontrol with an airworthy servocontrol that 
is marked with a letter ``R'' by the manufacturer after the S/N 
constitutes terminating action for the requirements of this AD.
    (f) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Manager, Safety Management Group, Rotorcraft 
Directorate, FAA, ATTN: Gary Roach, Aviation Safety Engineer, FAA, 
Regulations and Guidance Group, 2601 Meacham Blvd, Fort Worth, Texas 
76137, telephone (817) 222-5130, fax (817) 222 5961, for information 
about previously approved alternative methods of compliance.
    (g) The Joint Aircraft System/Component (JASC) Code is 6730: 
Rotorcraft Servo System.
    (h) This amendment becomes effective on November 14, 2011.

    Note 2:  The subject of this AD is addressed in European 
Aviation Safety Agency Emergency AD No. 2010-0117-E, dated June 16, 
2010.


    Issued in Fort Worth, Texas, on August 23, 2011.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011-27673 Filed 10-26-11; 8:45 am]
BILLING CODE 4910-13-P