Airworthiness Directives; Eurocopter France Model EC 130 B4 Helicopters, 47201-47203 [2010-17282]

Download as PDF Federal Register / Vol. 75, No. 150 / Thursday, August 5, 2010 / Rules and Regulations Revision G, dated December 8, 2009, under 5 U.S.C. 552(a) and 1 CFR part 51. (2) The Director of the Federal Register previously approved the incorporation by reference of TIMCO Service Bulletin TSB– 88–52–045, Revision E, dated November 6, 2008, on July 6, 2010 (75 FR 38017, July 1, 2010). (3) For service information identified in this AD, contact TIMCO Aviation Services, 815 Radar Road, Greensboro, North Carolina 27410–6221; telephone 336–668–4410, extension 3063; fax 336–662–8330; Internet: https://www.timco.aero. (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 NARA, call 202–741–6030, or go to https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on July 16, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–18620 Filed 8–4–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0713; Directorate Identifier 2009–SW–63–AD; Amendment 39– 16369; AD 2010–15–03] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Model EC 130 B4 Helicopters Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. AGENCY: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France helicopters. This action requires inspecting certain electrical harnesses for damage and if damage is found, repairing the electrical harness; protecting the electrical harness from damage; installing harness clamp blocks; and inspecting each fairing attachment screw to determine the length and replacing attachment screws, if they exceed a certain length. This amendment is prompted by a report of an in-flight incident that led to the inflation of the emergency floatation wwoods2 on DSK1DXX6B1PROD with RULES_PART 1 SUMMARY: VerDate Mar<15>2010 15:16 Aug 04, 2010 Jkt 220001 gear (emergency floats) and the activation of various warnings. The actions specified in this AD are intended to prevent interference between an electrical harness and the lower structure fairing attachment screws. Damage to an electrical harness by a lower structure fairing attachment screw could lead to short-circuiting of various warnings, inflation of the emergency floats during flight, and subsequent loss of control of the helicopter. DATES: Effective August 20, 2010. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of August 20, 2010. Comments for inclusion in the Rules Docket must be received on or before October 4, 2010. ADDRESSES: Use one of the following addresses to submit comments on this AD: • Federal eRulemaking Portal: Go to https://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 https:// www.eurocopter.com. Examining the Docket: You may examine the docket that contains the AD, any comments, and other information on the Internet at https:// 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: DOT/FAA Southwest Region, George Schwab, Aviation Safety Engineer, ASW–112, Rotorcraft Directorate, Safety Management Group, 2601 Meacham PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 47201 Blvd., Fort Worth, Texas 76137, telephone (817) 222–5114, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: Discussion This amendment adopts a new AD for Eurocopter France Model EC 130 B4 helicopters that have been modified in accordance with MOD 073774, and have not had MOD 073591 nor the modification specified in Eurocopter Drawing No. 350A085340 incorporated. This action requires, within 10 hours time-in-service (TIS), removing the lower forward right-hand, left-hand, and center lower structure fairings (fairings); inspecting each electrical harness for chaffing, tears, holes, or other damage at the location of each attachment screw and repairing any damage; protecting electrical harnesses by wrapping them with electrical tape; installing harness clamp blocks; and inspecting each attachment screw to determine the length and replacing any attachment screw that is longer than 14mm. This amendment is prompted by a report of an in-flight incident in which an attachment screw that secures the righthand lower center fairing damaged the electrical harness and caused several short circuits, resulting in the described incident. This condition, if not detected, could lead to inflation of the emergency floats during flight, and subsequent loss of control of the helicopter. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued AD No. 2006– 0344 R1, dated May 10, 2007, to correct an unsafe condition for Eurocopter France Model EC 130 B4 helicopters. EASA advises that their AD was initially issued as an Emergency AD, following a report of an in-flight incident which led to activation of various warning lights and inflation of the emergency floats. The pilot was able to land the helicopter without damage. EASA AD No. 2006–0344 R1 revises EASA Emergency AD 2006–0344–E, dated November 13, 2006. Related Service Information Eurocopter France has issued Emergency Alert Service Bulletin (EASB) No. 88A001 R1, dated April 17, 2007, which specifies procedures for detecting and correcting interference between an electrical harness and a fairing attachment screw. The EASA classified this EASB as mandatory and issued AD No. 2006–0344 R1, dated May 10, 2007, to ensure the continued airworthiness of these helicopters. E:\FR\FM\05AUR1.SGM 05AUR1 47202 Federal Register / Vol. 75, No. 150 / Thursday, August 5, 2010 / Rules and Regulations FAA’s Evaluation and Unsafe Condition Determination This helicopter has been approved by the aviation authority of France and is 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 the EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of this same type design. Differences Between This AD and the EASA AD This AD requires inspections by a qualified mechanic rather than checks, which may be conducted by a pilot. Also, this AD requires contacting the FAA, Safety Management Group, ASW– 112, instead of contacting Eurocopter France to define a certain customized repair solution before returning the helicopter to flight configuration if 4 or more electrical wires or cables need repair. Additionally, this AD uses the term ‘‘hours time-in-service’’ instead of ‘‘flight hours’’. wwoods2 on DSK1DXX6B1PROD with RULES_PART 1 FAA’s Determination and Requirements of This AD This unsafe condition is likely to exist or develop on other helicopters of the same type design. Therefore, this AD is being issued to prevent, on helicopters post MOD 073774, any interference between an electrical harness and an attachment screw. Embodiment of a modification in accordance with Eurocopter drawing 350A085342 is considered to be a temporary solution to be applied rapidly in order to ensure that there is no interference. Embodiment of a modification in accordance with Eurocopter Drawing 350A085340 is the permanent solution. The EASA AD has been revised to provide additional information that MOD 073591 also is a permanent solution and has been incorporated on new helicopters. This AD requires removing the fairings; inspecting each electrical harness for any chaffing, tear, hole, or other damage at the location of each attachment screw and repairing any damage; protecting electrical harnesses by wrapping them with electrical tape; installing harness clamp blocks; and inspecting each attachment screw to determine the length and replacing any that are longer than 14mm. Accomplish the actions by following specified portions of the EASB described previously. The short VerDate Mar<15>2010 15:16 Aug 04, 2010 Jkt 220001 compliance time involved is required because the previously described critical unsafe condition can adversely affect the controllability of the helicopter. Therefore, inspecting each electrical harness for damage at the location of each attachment screw and repairing any damage, if found; protecting the electrical harness by wrapping with electrical tape; installing harness clamp blocks; and inspecting each attachment screw to determine the length and replacing any that are longer than 14mm, are required within 10 hours time-in-service (TIS), a short compliance time, and this AD must be issued immediately. Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days. Costs of Compliance We estimate that this AD will affect about 13 helicopters of U.S. registry. We also estimate that it will take about 12 work-hours per helicopter to remove the lower structure fairings; inspect an electrical harness for interference and damage; repair an electrical harness, if necessary; shorten the attachment screws; install harness clamp blocks; and reinstall the lower fairings. The average labor rate is $85 per work-hour. Required parts will cost about $120 per helicopter. Based on these figures, we estimate the cost of this AD on U.S. operators is $1,140 per helicopter, $14,820 for the entire fleet. 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 ‘‘Docket No. FAA–2010–0713; Directorate Identifier 2009–SW–63–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 https:// 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 PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 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 this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the 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); and 3. 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. See the AD docket to examine the economic evaluation. 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, ■ E:\FR\FM\05AUR1.SGM 05AUR1 Federal Register / Vol. 75, No. 150 / Thursday, August 5, 2010 / Rules and Regulations 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 to read as follows: wwoods2 on DSK1DXX6B1PROD with RULES_PART 1 ■ 2010–15–03 Eurocopter France: Amendment 39–16369. Docket No. FAA–2010–0713; Directorate Identifier 2009–SW–63–AD. Applicability: Model EC 130 B4 helicopters that have been modified in accordance with MOD 073774, and have not had MOD 073591 nor the modification specified in Eurocopter Drawing No. 350A085340 incorporated, certificated in any category. Compliance: Required within 10 hours time-in-service (TIS), unless accomplished previously. To detect interference and prevent damage to an electrical harness by a lower structure fairing attachment screw (attachment screw), which could lead to short-circuiting of various warnings, inflation of the emergency floatation gear (emergency floats) during flight, and subsequent loss of control of the helicopter, accomplish the following: (a) Remove the lower forward right-hand, left-hand, and center fairings. (b) Inspect each electrical harness for chaffing, a tear, a hole, or other damage at the location of each attachment screw as depicted in Details B, C, and D in Figure 1 in Eurocopter Emergency Alert Service Bulletin No. 88A001 R1, dated April 17, 2007 (EASB), and as shown at point (a) in Figure 2 and Figure 3 in the EASB. (1) If there is no chaffing, tear, hole, or other damage to the electrical harness at any attachment screw: (i) Determine the length of each attachment screw that secures the fairings. Replace any attachment screw that is longer than 14mm with an airworthy attachment screw, part number (P/N) A0164TK050S014X; (ii) Install the spacer on the electrical harness in accordance with paragraph 2.B.3.a. of the Accomplishment Instructions of the EASB; (iii) Relocate the electrical harness on the cable holders in accordance with paragraph 2.B.3.b. of the Accomplishment Instructions of the EASB; and (iv) Install the harness clamp blocks in accordance with paragraph 2.B.4. of the Accomplishment Instructions of the EASB. (2) If there is chaffing, a tear, a hole, or other damage to an electrical harness at the location of an attachment screw, remove any protective tape from the electrical harness as shown at point (b) in Figure 2 of the EASB and inspect the insulation on each electrical wire and cable strand for chaffing, a tear, a hole, or other damage at the attachment screw location. VerDate Mar<15>2010 15:16 Aug 04, 2010 Jkt 220001 (i) If there is no chaffing, tear, hole, or other damage to the insulation on any wire or cable strand, wrap the electrical harness with protective tape and comply with paragraphs (b)(1)(i) through (b)(1)(iv) of this AD. (ii) If there is chaffing, a tear, a hole, or other damage to the insulation on any electrical wire or cable strand, but the electrical wire or cable strand is not damaged, wrap the electrical wire or cable strand that has damaged insulation with protective tape and wrap the electrical harness with protective tape, then comply with paragraphs (b)(1)(i) through (b)(1)(iv) of this AD. (c) If 3 or less electrical wires or cable strands in the same immediate area are damaged: (1) Repair each damaged electrical wire or cable strand with an extension lead, P/N E0541–10, in accordance with the Appendix to the EASB; test the electrical continuity of the repaired electrical wire or cable strand using an ohmmeter, continuity test light, or equivalent device; and functionally test the system affected by the repair; (2) Wrap the electrical harness with protective tape; and (3) Comply with paragraphs (b)(1)(i) through (b)(1)(iv) of this AD. (d) If 4 or more electrical wires or cable strands in the same immediate area are damaged: (1) Contact the Safety Management Group, Rotorcraft Directorate, FAA, ATTN: George Schwab, Aviation Safety Engineer, 2601 Meacham Blvd., Fort Worth, Texas, 76137, telephone (817) 222–5114, fax (817) 222– 5961, for an approved electrical conductor repair procedure; and (2) Comply with (b)(1)(i) through (b)(1)(iv) of this AD. (e) Reinstall the fairings. (f) Contact the Manager, Safety Management Group, Rotorcraft Directorate, FAA, ATTN: George Schwab, Aviation Safety Engineer, 2601 Meacham Blvd., Fort Worth, Texas, 76137, telephone (817) 222–5114, fax (817) 222–5961, for information about previously approved alternative methods of compliance. (g) The Joint Aircraft System/Component (JASC) Code is 3297: Landing Gear System Wiring. (h) The inspections, modifications and repairs, if needed, shall be done in accordance with the specified portions of Eurocopter Emergency Alert Service Bulletin No. 88A001 R1, dated April 17, 2007. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 75053–4005, telephone (800) 232–0323, fax (972) 641–3710, or at https://www.eurocopter.com. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas or 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: https://www.archives. gov/federal_register/code_of_federal_ regulations/ibr_locations.html. PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 47203 (i) This amendment becomes effective on August 20, 2010. Note: The subject of this AD is addressed in European Aviation Safety Agency (France) AD No. 2006–0344 R1, dated May 10, 2007, which revises European Aviation Safety Agency Emergency AD No. 2006–0344–E, dated November 13, 2006. Issued in Fort Worth, Texas, on July 8, 2010. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2010–17282 Filed 8–4–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0403; Directorate Identifier 2007–NM–166–AD; Amendment 39–16379; AD 2010–16–03] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Corporation Model MD–11 and MD–11F Airplanes Equipped With General Electric CF6–80C2 Series Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Model MD–11 and MD–11F airplanes. This AD requires revising the airplane flight manual to advise the flightcrew to use certain procedures during descent in certain icing conditions. This AD results from reports of several in-flight engine flameouts, including multiple dual engine flameout events, in icecrystal icing conditions. We are issuing this AD to ensure that the flightcrew has the proper procedures to follow in certain icing conditions. These certain icing conditions could cause a multiple engine flameout during flight with the potential inability to restart the engines, and consequent forced landing of the airplane. SUMMARY: DATES: This AD is effective September 9, 2010. Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 AD, the regulatory evaluation, any comments received, and E:\FR\FM\05AUR1.SGM 05AUR1

Agencies

[Federal Register Volume 75, Number 150 (Thursday, August 5, 2010)]
[Rules and Regulations]
[Pages 47201-47203]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-17282]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0713; Directorate Identifier 2009-SW-63-AD; 
Amendment 39-16369; AD 2010-15-03]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model EC 130 B4 
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 France helicopters. This action requires 
inspecting certain electrical harnesses for damage and if damage is 
found, repairing the electrical harness; protecting the electrical 
harness from damage; installing harness clamp blocks; and inspecting 
each fairing attachment screw to determine the length and replacing 
attachment screws, if they exceed a certain length. This amendment is 
prompted by a report of an in-flight incident that led to the inflation 
of the emergency floatation gear (emergency floats) and the activation 
of various warnings. The actions specified in this AD are intended to 
prevent interference between an electrical harness and the lower 
structure fairing attachment screws. Damage to an electrical harness by 
a lower structure fairing attachment screw could lead to short-
circuiting of various warnings, inflation of the emergency floats 
during flight, and subsequent loss of control of the helicopter.

DATES: Effective August 20, 2010.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 20, 2010.
    Comments for inclusion in the Rules Docket must be received on or 
before October 4, 2010.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
     Federal eRulemaking Portal: Go to https://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 https://www.eurocopter.com.
    Examining the Docket: You may examine the docket that contains the 
AD, any comments, and other information on the Internet at https://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: DOT/FAA Southwest Region, George 
Schwab, Aviation Safety Engineer, ASW-112, Rotorcraft Directorate, 
Safety Management Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, 
telephone (817) 222-5114, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION:

Discussion

    This amendment adopts a new AD for Eurocopter France Model EC 130 
B4 helicopters that have been modified in accordance with MOD 073774, 
and have not had MOD 073591 nor the modification specified in 
Eurocopter Drawing No. 350A085340 incorporated. This action requires, 
within 10 hours time-in-service (TIS), removing the lower forward 
right-hand, left-hand, and center lower structure fairings (fairings); 
inspecting each electrical harness for chaffing, tears, holes, or other 
damage at the location of each attachment screw and repairing any 
damage; protecting electrical harnesses by wrapping them with 
electrical tape; installing harness clamp blocks; and inspecting each 
attachment screw to determine the length and replacing any attachment 
screw that is longer than 14mm. This amendment is prompted by a report 
of an in-flight incident in which an attachment screw that secures the 
right-hand lower center fairing damaged the electrical harness and 
caused several short circuits, resulting in the described incident. 
This condition, if not detected, could lead to inflation of the 
emergency floats during flight, and subsequent loss of control of the 
helicopter.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued AD 
No. 2006-0344 R1, dated May 10, 2007, to correct an unsafe condition 
for Eurocopter France Model EC 130 B4 helicopters. EASA advises that 
their AD was initially issued as an Emergency AD, following a report of 
an in-flight incident which led to activation of various warning lights 
and inflation of the emergency floats. The pilot was able to land the 
helicopter without damage. EASA AD No. 2006-0344 R1 revises EASA 
Emergency AD 2006-0344-E, dated November 13, 2006.

Related Service Information

    Eurocopter France has issued Emergency Alert Service Bulletin 
(EASB) No. 88A001 R1, dated April 17, 2007, which specifies procedures 
for detecting and correcting interference between an electrical harness 
and a fairing attachment screw. The EASA classified this EASB as 
mandatory and issued AD No. 2006-0344 R1, dated May 10, 2007, to ensure 
the continued airworthiness of these helicopters.

[[Page 47202]]

FAA's Evaluation and Unsafe Condition Determination

    This helicopter has been approved by the aviation authority of 
France and is 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 the EASA and determined the unsafe condition 
exists and is likely to exist or develop on other helicopters of this 
same type design.

Differences Between This AD and the EASA AD

    This AD requires inspections by a qualified mechanic rather than 
checks, which may be conducted by a pilot. Also, this AD requires 
contacting the FAA, Safety Management Group, ASW-112, instead of 
contacting Eurocopter France to define a certain customized repair 
solution before returning the helicopter to flight configuration if 4 
or more electrical wires or cables need repair. Additionally, this AD 
uses the term ``hours time-in-service'' instead of ``flight hours''.

FAA's Determination and Requirements of This AD

    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design. Therefore, this AD is being issued 
to prevent, on helicopters post MOD 073774, any interference between an 
electrical harness and an attachment screw. Embodiment of a 
modification in accordance with Eurocopter drawing 350A085342 is 
considered to be a temporary solution to be applied rapidly in order to 
ensure that there is no interference. Embodiment of a modification in 
accordance with Eurocopter Drawing 350A085340 is the permanent 
solution. The EASA AD has been revised to provide additional 
information that MOD 073591 also is a permanent solution and has been 
incorporated on new helicopters. This AD requires removing the 
fairings; inspecting each electrical harness for any chaffing, tear, 
hole, or other damage at the location of each attachment screw and 
repairing any damage; protecting electrical harnesses by wrapping them 
with electrical tape; installing harness clamp blocks; and inspecting 
each attachment screw to determine the length and replacing any that 
are longer than 14mm.
    Accomplish the actions by following specified portions of the EASB 
described previously. The short compliance time involved is required 
because the previously described critical unsafe condition can 
adversely affect the controllability of the helicopter. Therefore, 
inspecting each electrical harness for damage at the location of each 
attachment screw and repairing any damage, if found; protecting the 
electrical harness by wrapping with electrical tape; installing harness 
clamp blocks; and inspecting each attachment screw to determine the 
length and replacing any that are longer than 14mm, are required within 
10 hours time-in-service (TIS), a short compliance time, and this AD 
must be issued immediately.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Costs of Compliance

    We estimate that this AD will affect about 13 helicopters of U.S. 
registry. We also estimate that it will take about 12 work-hours per 
helicopter to remove the lower structure fairings; inspect an 
electrical harness for interference and damage; repair an electrical 
harness, if necessary; shorten the attachment screws; install harness 
clamp blocks; and reinstall the lower fairings. The average labor rate 
is $85 per work-hour. Required parts will cost about $120 per 
helicopter. Based on these figures, we estimate the cost of this AD on 
U.S. operators is $1,140 per helicopter, $14,820 for the entire fleet.

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 ``Docket No. FAA-2010-0713; Directorate 
Identifier 2009-SW-63-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 https://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 this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national Government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the 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); and
    3. 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. See the AD docket to examine the economic evaluation.

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

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator,

[[Page 47203]]

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 to 
read as follows:

2010-15-03 Eurocopter France: Amendment 39-16369. Docket No. FAA-
2010-0713; Directorate Identifier 2009-SW-63-AD.
    Applicability: Model EC 130 B4 helicopters that have been 
modified in accordance with MOD 073774, and have not had MOD 073591 
nor the modification specified in Eurocopter Drawing No. 350A085340 
incorporated, certificated in any category.
    Compliance: Required within 10 hours time-in-service (TIS), 
unless accomplished previously.
    To detect interference and prevent damage to an electrical 
harness by a lower structure fairing attachment screw (attachment 
screw), which could lead to short-circuiting of various warnings, 
inflation of the emergency floatation gear (emergency floats) during 
flight, and subsequent loss of control of the helicopter, accomplish 
the following:
    (a) Remove the lower forward right-hand, left-hand, and center 
fairings.
    (b) Inspect each electrical harness for chaffing, a tear, a 
hole, or other damage at the location of each attachment screw as 
depicted in Details B, C, and D in Figure 1 in Eurocopter Emergency 
Alert Service Bulletin No. 88A001 R1, dated April 17, 2007 (EASB), 
and as shown at point (a) in Figure 2 and Figure 3 in the EASB.
    (1) If there is no chaffing, tear, hole, or other damage to the 
electrical harness at any attachment screw:
    (i) Determine the length of each attachment screw that secures 
the fairings. Replace any attachment screw that is longer than 14mm 
with an airworthy attachment screw, part number (P/N) 
A0164TK050S014X;
    (ii) Install the spacer on the electrical harness in accordance 
with paragraph 2.B.3.a. of the Accomplishment Instructions of the 
EASB;
    (iii) Relocate the electrical harness on the cable holders in 
accordance with paragraph 2.B.3.b. of the Accomplishment 
Instructions of the EASB; and
    (iv) Install the harness clamp blocks in accordance with 
paragraph 2.B.4. of the Accomplishment Instructions of the EASB.
    (2) If there is chaffing, a tear, a hole, or other damage to an 
electrical harness at the location of an attachment screw, remove 
any protective tape from the electrical harness as shown at point 
(b) in Figure 2 of the EASB and inspect the insulation on each 
electrical wire and cable strand for chaffing, a tear, a hole, or 
other damage at the attachment screw location.
    (i) If there is no chaffing, tear, hole, or other damage to the 
insulation on any wire or cable strand, wrap the electrical harness 
with protective tape and comply with paragraphs (b)(1)(i) through 
(b)(1)(iv) of this AD.
    (ii) If there is chaffing, a tear, a hole, or other damage to 
the insulation on any electrical wire or cable strand, but the 
electrical wire or cable strand is not damaged, wrap the electrical 
wire or cable strand that has damaged insulation with protective 
tape and wrap the electrical harness with protective tape, then 
comply with paragraphs (b)(1)(i) through (b)(1)(iv) of this AD.
    (c) If 3 or less electrical wires or cable strands in the same 
immediate area are damaged:
    (1) Repair each damaged electrical wire or cable strand with an 
extension lead, P/N E0541-10, in accordance with the Appendix to the 
EASB; test the electrical continuity of the repaired electrical wire 
or cable strand using an ohmmeter, continuity test light, or 
equivalent device; and functionally test the system affected by the 
repair;
    (2) Wrap the electrical harness with protective tape; and
    (3) Comply with paragraphs (b)(1)(i) through (b)(1)(iv) of this 
AD.
    (d) If 4 or more electrical wires or cable strands in the same 
immediate area are damaged:
    (1) Contact the Safety Management Group, Rotorcraft Directorate, 
FAA, ATTN: George Schwab, Aviation Safety Engineer, 2601 Meacham 
Blvd., Fort Worth, Texas, 76137, telephone (817) 222-5114, fax (817) 
222-5961, for an approved electrical conductor repair procedure; and
    (2) Comply with (b)(1)(i) through (b)(1)(iv) of this AD.
    (e) Reinstall the fairings.
    (f) Contact the Manager, Safety Management Group, Rotorcraft 
Directorate, FAA, ATTN: George Schwab, Aviation Safety Engineer, 
2601 Meacham Blvd., Fort Worth, Texas, 76137, telephone (817) 222-
5114, fax (817) 222-5961, for information about previously approved 
alternative methods of compliance.
    (g) The Joint Aircraft System/Component (JASC) Code is 3297: 
Landing Gear System Wiring.
    (h) The inspections, modifications and repairs, if needed, shall 
be done in accordance with the specified portions of Eurocopter 
Emergency Alert Service Bulletin No. 88A001 R1, dated April 17, 
2007. The Director of the Federal Register approved this 
incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 
CFR part 51. Copies may be obtained from American Eurocopter 
Corporation, 2701 Forum Drive, Grand Prairie, TX 75053-4005, 
telephone (800) 232-0323, fax (972) 641-3710, or at https://www.eurocopter.com. Copies may be inspected at the FAA, Office of 
the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas or 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: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
    (i) This amendment becomes effective on August 20, 2010.

    Note:  The subject of this AD is addressed in European Aviation 
Safety Agency (France) AD No. 2006-0344 R1, dated May 10, 2007, 
which revises European Aviation Safety Agency Emergency AD No. 2006-
0344-E, dated November 13, 2006.


    Issued in Fort Worth, Texas, on July 8, 2010.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-17282 Filed 8-4-10; 8:45 am]
BILLING CODE 4910-13-P
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