Airworthiness Directives; Eurocopter Deutschland GmbH Helicopters, 42958-42962 [2012-17559]

Download as PDF 42958 Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations (ii) If the serial number is not listed in the table in paragraph 3.B.(2) of Bombardier Service Bulletin 8–32–170, dated February 25, 2011: Within 2,000 flight hours or 12 months after the effective date of this AD, whichever occurs first, replace the accumulator with a new non-suspect accumulator, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–32–172, dated March 15, 2011. (h) Parts Installation Prohibition As of the effective date of this AD, no person may install a parking brake accumulator, P/N 0860162001 or 0860162002 with a serial number that is not listed in the table in paragraph 3.B.(2) of Bombardier Service Bulletin 8–32–170, dated February 25, 2011, on any airplane. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone 516–228–7300; fax 516– 794–5531. 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) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. mstockstill on DSK4VPTVN1PROD with RULES (j) Related Information Refer to MCAI Canadian Airworthiness Directive CF–2011–29, dated August 2, 2011, and the service information identified in paragraphs (j)(1) and (j)(2) of this AD, for related information. (1) Bombardier Service Bulletin 8–32–170, dated February 25, 2011. (2) Bombardier Service Bulletin 8–32–172, dated March 15, 2011. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. (i) Bombardier Service Bulletin 8–32–170, dated February 25, 2011. VerDate Mar<15>2010 16:44 Jul 20, 2012 Jkt 226001 (ii) Bombardier Service Bulletin 8–32–172, dated March 15, 2011. (3) For service information identified in this AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539; email thd.qseries@aero.bombardier.com; Internet http://www.bombardier.com. (4) You may review copies of the 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. (5) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202–741– 6030, or go to http://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. The Director of the Federal Register approved the incorporation by reference of certain documents August 7, 2012. We must receive comments on this AD by September 21, 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. Issued in Renton, Washington, on June 28, 2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. Examining the AD Docket [FR Doc. 2012–16967 Filed 7–20–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0704; Directorate Identifier 2012–SW–040–AD; Amendment 39–17113; AD 2012–13–11] RIN 2120–AA64 Airworthiness Directives; Eurocopter Deutschland GmbH Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model MBB–BK 117 (all versions) and BO–105LS A–3 helicopters. This AD requires inspecting the tail rotor pitch link spherical bearing for proper swaging. This AD is prompted by a report of a tail rotor pitch link with a spherical bearing that had migrated out of the bearing bore. The actions specified by this AD are intended to prevent failure of the tail rotor pitch link and subsequent loss of control of the helicopter. DATES: This AD becomes effective August 7, 2012. SUMMARY: PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 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 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 AD, contact Able Engineering and Support Services, 2920 East Chambers Street, Phoenix, AZ 85040; telephone (602) 304–1227; fax (602) 304–1277; email info@ableengineering.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: Sharon Miles, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222–5110; email sharon.y.miles@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, 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 E:\FR\FM\23JYR1.SGM 23JYR1 Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, 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 them 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 rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments. Discussion Able Engineering & Component Services (Able) received a report of a tail rotor pitch link with a spherical bearing that had migrated out of the bearing bore. Investigation by Able revealed that the migration resulted from the spherical bearing being improperly swaged during a repair process and that the affected parts were limited to those repaired after January 1, 2011. Able determined that an inspection of other tail rotor pitch links repaired after that date is necessary to determine their airworthiness and issued Alert Service Bulletin (ASB) No.: 2012–001, Revision IR, dfated March 7, 2012 (Able ASB). On March 19, 2012, Eurocopter issued one ASB with multiple numbers: Eurocopter Emergency Alert Service Bulletin (EASB) No. BO105 LS–30A– 013 for model BO–105LS A–3 helicopters; EASB No. BO105 LS A–3– STC–0654/3058–30A–001 for model BO–105LS A–3 Superlifter helicopters; EASB No. MBB–BK117–30A–115 for model MBB–BK 117 A–1, A–3, A–4, B– 1, B–2, and C–1 helicopters; and EASB No. MBB–BK117 C–2–67A–016 for model MBB–BK117 C–2 helicopters, all Revision 0. The EASB specifies complying with the inspection described in the Able ASB. mstockstill on DSK4VPTVN1PROD with RULES FAA’s Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other helicopters of these same type designs. Related Service Information We reviewed the Able ASB, which identifies certain tail rotor pitch links (pitch links) that are affected by the improper swaging of the spherical bearings. The Able ASB describes procedures to remove the pitch links VerDate Mar<15>2010 16:44 Jul 20, 2012 Jkt 226001 and visually inspect the spherical bearings with an 8X magnifying glass for a bearing that has not been swaged and will migrate out of the bearing bore. If a pitch link is discovered with a bearing not properly swaged, the Able ASB specifies removing the pitch link from service and returning it to Able Engineering. AD Requirements This AD requires: • Removing the pitch link from the helicopter and cleaning the spherical bearings. • Applying hand pressure to the bearing faces and inspecting with an 8X or higher power magnifying glass for complete swaging of the bearing bore. • If the pitch link has not been completely swaged, removing the pitch link and replacing it with an airworthy pitch link. Differences Between This AD and the Service Information The service information requires returning unairworthy pitch links to Able Engineering; this AD does not. The Eurocopter ASB applies to the Model BO105 LS A–3 ‘‘Superlifter,’’ and this AD does not as that model is not type certificated in the U.S. Costs of Compliance We estimate that this AD will affect 130 helicopters of U.S. Registry, and that operators may incur the following costs in order to comply with this AD. Inspecting each pitch link will require about 1.5 work hours at an average labor rate of $85 per hour, for a total cost per helicopter of about $127 and a cost to the U.S. operator fleet of $16,510. If required, replacing a pitch link with an airworthy pitch link will require about 1.5 work hours at an average labor rate of $85 per hour, and required parts will cost $1,442, for a total cost per helicopter of about $1,569. FAA’s Justification and Determination of the Effective Date Providing an opportunity for public comments prior to adopting these AD requirements would delay implementing the safety actions needed to correct this known unsafe condition. Therefore, we find that the risk to the flying public justifies waiving notice and comment prior to the adoption of this rule because some of the corrective actions must be accomplished before further flight. Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and opportunity for public comment before issuing this AD are impracticable and PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 42959 that good cause exists for making this amendment effective in less than 30 days. 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, 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: E:\FR\FM\23JYR1.SGM 23JYR1 42960 Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations 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): ■ 2012–13–11 Eurocopter Deutschland GmbH Helicopters: Amendment 39–17113; Docket No. FAA–2012–0704; Directorate Identifier 2012–SW–040–AD. (a) Applicability mstockstill on DSK4VPTVN1PROD with RULES This AD applies to Eurocopter Deutschland GmbH (ECD) Model MBB–BK 117 A–1, VerDate Mar<15>2010 18:14 Jul 20, 2012 Jkt 226001 MBB–BK 117 A–3, MBB–BK 117 A–4, MBB– BK 117 B–1, MBB–BK 117 B–2, MBB–BK 117 C–1, MBB–BK 117 C–2, and BO–105LS A–3 helicopters, with a tail rotor pitch link (pitch link) part number (P/N) 117–31821, 117– 31822, or B642M1018101 with a serial number listed in Appendix 1 of Able Engineering & Component Services (Able) Alert Service Bulletin (ASB) No. 2012–001, Revision IR, dated March 7, 2012, installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as an improperly swaged spherical bearing on the pitch link, which could result in loss of tail rotor control and subsequent loss of control of the helicopter. PO 00000 Frm 00012 Fmt 4700 Sfmt 4725 (c) Effective Date This AD becomes August 7, 2012. (d) 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. (e) Required Actions For pitch links installed within the last 10 hours time-in-service (TIS), before further flight; for all other affected pitch links, within the next 10 hours TIS: (1) Remove the pitch link. (2) Clean the area around the spherical bearings and pitch link bearing bore chamfer. (3) Apply axial hand pressure to the faces of both spherical bearings as shown in Figure 1 to Paragraph (e) of this AD. E:\FR\FM\23JYR1.SGM 23JYR1 ER23JY12.000</GPH> PART 39—AIRWORTHINESS DIRECTIVES Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations 42961 chamfer as shown in Figure 2 to Paragraph (e) of this AD. bearing and the chamfer, as shown in Figure 3 to Paragraph (e) of this AD, replace the pitch link with an airworthy pitch link. VerDate Mar<15>2010 18:14 Jul 20, 2012 Jkt 226001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\23JYR1.SGM 23JYR1 ER23JY12.001</GPH> chamfer surface. Determine that the bearings have been completely swaged and there is no gap between the edge of the bearing and the (5) If a bearing is not completely swaged or there is a gap between the edge of the mstockstill on DSK4VPTVN1PROD with RULES (4) Using an 8X or higher power magnifying glass, inspect the boundaries between the bearing and the bearing bore Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations (f) Special Flight Permits Special flight permits will not be issued. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Sharon Miles, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222–5110; email sharon.y.miles@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. mstockstill on DSK4VPTVN1PROD with RULES (h) Subject Joint Aircraft Service Component (JASC) Code: 6420: Tail Rotor Head. (i) 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 the AD specifies otherwise. VerDate Mar<15>2010 16:44 Jul 20, 2012 Jkt 226001 (i) Able Engineering & Component Services Alert Service Bulletin No. 2012–001, Revision IR, dated March 7, 2012. (ii) Reserved. (3) For Able Engineering & Component Services service information identified in this AD, contact Able Engineering & Component Services, 2920 East Chambers Street, Phoenix, AZ 85040; telephone (602) 304–1227; fax (602) 304–1277; email info@ableengineering.com. (4) You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (5) You may also view this service information 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/ code_of_federal_regulations/ibr_ locations.html. Issued in Fort Worth, Texas, on July 2, 2012. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2012–17559 Filed 7–20–12; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0149; Directorate Identifier 2011–NM–255–AD; Amendment 39–17117; AD 2012–14–03] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777–200 and –300 series airplanes. This AD was prompted by reports of fatigue cracks in the lap joints, which initiated at scribe lines that were made during production when maskant was removed from the affected skin panels during the chemical milling process. This AD requires repetitive external phased-array ultrasonic inspections to detect cracks of the affected fuselage skin lap splices in Sections 41, 43, and 44, as applicable, and repair if necessary. We are issuing SUMMARY: E:\FR\FM\23JYR1.SGM 23JYR1 ER23JY12.002</GPH> 42962

Agencies

[Federal Register Volume 77, Number 141 (Monday, July 23, 2012)]
[Rules and Regulations]
[Pages 42958-42962]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-17559]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0704; Directorate Identifier 2012-SW-040-AD; 
Amendment 39-17113; AD 2012-13-11]
RIN 2120-AA64


Airworthiness Directives; Eurocopter Deutschland GmbH Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for 
Eurocopter Deutschland GmbH (ECD) Model MBB-BK 117 (all versions) and 
BO-105LS A-3 helicopters. This AD requires inspecting the tail rotor 
pitch link spherical bearing for proper swaging. This AD is prompted by 
a report of a tail rotor pitch link with a spherical bearing that had 
migrated out of the bearing bore. The actions specified by this AD are 
intended to prevent failure of the tail rotor pitch link and subsequent 
loss of control of the helicopter.

DATES: This AD becomes effective August 7, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents August 7, 2012.
    We must receive comments on this AD by September 21, 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 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 AD, contact Able 
Engineering and Support Services, 2920 East Chambers Street, Phoenix, 
AZ 85040; telephone (602) 304-1227; fax (602) 304-1277; email 
info@ableengineering.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: Sharon Miles, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222-5110; 
email sharon.y.miles@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments prior to it becoming effective. However, 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

[[Page 42959]]

federalism impacts that resulted from adopting this AD. The most 
helpful comments reference a specific portion of the AD, 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 them 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 rulemaking during the comment period. We will consider 
all the comments we receive and may conduct additional rulemaking based 
on those comments.

Discussion

    Able Engineering & Component Services (Able) received a report of a 
tail rotor pitch link with a spherical bearing that had migrated out of 
the bearing bore. Investigation by Able revealed that the migration 
resulted from the spherical bearing being improperly swaged during a 
repair process and that the affected parts were limited to those 
repaired after January 1, 2011. Able determined that an inspection of 
other tail rotor pitch links repaired after that date is necessary to 
determine their airworthiness and issued Alert Service Bulletin (ASB) 
No.: 2012-001, Revision IR, dfated March 7, 2012 (Able ASB).
    On March 19, 2012, Eurocopter issued one ASB with multiple numbers: 
Eurocopter Emergency Alert Service Bulletin (EASB) No. BO105 LS-30A-013 
for model BO-105LS A-3 helicopters; EASB No. BO105 LS A-3-STC-0654/
3058-30A-001 for model BO-105LS A-3 Superlifter helicopters; EASB No. 
MBB-BK117-30A-115 for model MBB-BK 117 A-1, A-3, A-4, B-1, B-2, and C-1 
helicopters; and EASB No. MBB-BK117 C-2-67A-016 for model MBB-BK117 C-2 
helicopters, all Revision 0. The EASB specifies complying with the 
inspection described in the Able ASB.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other helicopters of these same type 
designs.

Related Service Information

    We reviewed the Able ASB, which identifies certain tail rotor pitch 
links (pitch links) that are affected by the improper swaging of the 
spherical bearings. The Able ASB describes procedures to remove the 
pitch links and visually inspect the spherical bearings with an 8X 
magnifying glass for a bearing that has not been swaged and will 
migrate out of the bearing bore. If a pitch link is discovered with a 
bearing not properly swaged, the Able ASB specifies removing the pitch 
link from service and returning it to Able Engineering.

AD Requirements

    This AD requires:
     Removing the pitch link from the helicopter and cleaning 
the spherical bearings.
     Applying hand pressure to the bearing faces and inspecting 
with an 8X or higher power magnifying glass for complete swaging of the 
bearing bore.
     If the pitch link has not been completely swaged, removing 
the pitch link and replacing it with an airworthy pitch link.

Differences Between This AD and the Service Information

    The service information requires returning unairworthy pitch links 
to Able Engineering; this AD does not. The Eurocopter ASB applies to 
the Model BO105 LS A-3 ``Superlifter,'' and this AD does not as that 
model is not type certificated in the U.S.

Costs of Compliance

    We estimate that this AD will affect 130 helicopters of U.S. 
Registry, and that operators may incur the following costs in order to 
comply with this AD. Inspecting each pitch link will require about 1.5 
work hours at an average labor rate of $85 per hour, for a total cost 
per helicopter of about $127 and a cost to the U.S. operator fleet of 
$16,510. If required, replacing a pitch link with an airworthy pitch 
link will require about 1.5 work hours at an average labor rate of $85 
per hour, and required parts will cost $1,442, for a total cost per 
helicopter of about $1,569.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments prior to adopting 
these AD requirements would delay implementing the safety actions 
needed to correct this known unsafe condition. Therefore, we find that 
the risk to the flying public justifies waiving notice and comment 
prior to the adoption of this rule because some of the corrective 
actions must be accomplished before further flight.
    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we determined that notice and opportunity for 
public comment before issuing this AD are impracticable and that good 
cause exists for making this amendment effective in less than 30 days.

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, 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.

Adoption of the Amendment

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

[[Page 42960]]

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):

2012-13-11 Eurocopter Deutschland GmbH Helicopters: Amendment 39-
17113; Docket No. FAA-2012-0704; Directorate Identifier 2012-SW-040-
AD.

(a) Applicability

    This AD applies to Eurocopter Deutschland GmbH (ECD) Model MBB-
BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A-4, MBB-BK 117 B-1, MBB-BK 
117 B-2, MBB-BK 117 C-1, MBB-BK 117 C-2, and BO-105LS A-3 
helicopters, with a tail rotor pitch link (pitch link) part number 
(P/N) 117-31821, 117-31822, or B642M1018101 with a serial number 
listed in Appendix 1 of Able Engineering & Component Services (Able) 
Alert Service Bulletin (ASB) No. 2012-001, Revision IR, dated March 
7, 2012, installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as an improperly swaged 
spherical bearing on the pitch link, which could result in loss of 
tail rotor control and subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes August 7, 2012.

(d) 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.

(e) Required Actions

    For pitch links installed within the last 10 hours time-in-
service (TIS), before further flight; for all other affected pitch 
links, within the next 10 hours TIS:
    (1) Remove the pitch link.
    (2) Clean the area around the spherical bearings and pitch link 
bearing bore chamfer.
    (3) Apply axial hand pressure to the faces of both spherical 
bearings as shown in Figure 1 to Paragraph (e) of this AD.
[GRAPHIC] [TIFF OMITTED] TR23JY12.000


[[Page 42961]]


    (4) Using an 8X or higher power magnifying glass, inspect the 
boundaries between the bearing and the bearing bore chamfer surface. 
Determine that the bearings have been completely swaged and there is 
no gap between the edge of the bearing and the chamfer as shown in 
Figure 2 to Paragraph (e) of this AD.
[GRAPHIC] [TIFF OMITTED] TR23JY12.001

    (5) If a bearing is not completely swaged or there is a gap 
between the edge of the bearing and the chamfer, as shown in Figure 
3 to Paragraph (e) of this AD, replace the pitch link with an 
airworthy pitch link.

[[Page 42962]]

[GRAPHIC] [TIFF OMITTED] TR23JY12.002

(f) Special Flight Permits

    Special flight permits will not be issued.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Sharon Miles, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222-5110; 
email sharon.y.miles@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.

 (h) Subject

    Joint Aircraft Service Component (JASC) Code: 6420: Tail Rotor 
Head.

(i) 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 the AD specifies otherwise.
    (i) Able Engineering & Component Services Alert Service Bulletin 
No. 2012-001, Revision IR, dated March 7, 2012.
    (ii) Reserved.
    (3) For Able Engineering & Component Services service 
information identified in this AD, contact Able Engineering & 
Component Services, 2920 East Chambers Street, Phoenix, AZ 85040; 
telephone (602) 304-1227; fax (602) 304-1277; email 
info@ableengineering.com.
    (4) You may view this service information at the FAA, Office of 
the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137.
    (5) You may also view this service information 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/code_of_federal_regulations/ibr_locations.html.

    Issued in Fort Worth, Texas, on July 2, 2012.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-17559 Filed 7-20-12; 8:45 am]
BILLING CODE 4910-13-P