Airworthiness Directives; Eurocopter France Helicopters, 23686-23688 [2013-09414]

Download as PDF 23686 Federal Register / Vol. 78, No. 77 / Monday, April 22, 2013 / Proposed Rules 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6467; fax: 425–917–6590; email: raymont.mei@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We proposed to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) with a notice of proposed rulemaking (NPRM) for a new AD for certain Model 777–200 and –300 series airplanes. That NPRM published in the Federal Register on March 8, 2011 (76 FR 12617). The NPRM would have required removing the electrical system control panel, changing the wiring, installing a new electrical power control panel, and installing new operational software for the electrical load management system and configuration database. The NPRM resulted from an in-flight entertainment (IFE) systems review. The proposed actions were intended to ensure that the flightcrew is able to turn off electrical power to the IFE system and other non-essential electrical systems through a switch in the flight compartment in the event of smoke or flames. In the event of smoke or flames in the airplane flight deck or passenger cabin, the flightcrew’s inability to turn off electrical power to the IFE system and other non-essential electrical systems could result in the inability to control smoke or flames in the airplane flight deck or passenger cabin during a non-normal or emergency situation. Actions Since NPRM (76 FR 12617, March 8, 2011) Was Issued tkelley on DSK3SPTVN1PROD with PROPOSALS FAA’s Conclusions Upon further consideration, we have determined that the unsafe condition still exists, however, we intend to address it with new AD rulemaking. Accordingly, the NPRM (76 FR 12617, March 8, 2011) is withdrawn. Withdrawal of the NPRM (76 FR 12617, March 8, 2011) does not preclude the FAA from issuing another related action or commit the FAA to any course of action in the future. 16:36 Apr 19, 2013 Jkt 229001 Since this action only withdraws an NPRM (76 FR 12617, March 8, 2011), it is neither a proposed nor a final rule and therefore is not covered under Executive Order 12866, the Regulatory Flexibility Act, or DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Withdrawal Accordingly, we withdraw the NPRM, Docket No. FAA–2011–0153, Directorate Identifier 2010–NM–022–AD, which published in the Federal Register on March 8, 2011 (76 FR 12617). Issued in Renton, Washington, on February 1, 2013. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–09418 Filed 4–19–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0353; Directorate Identifier 2008–SW–029–AD] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: Since we issued the NPRM (76 FR 12617, March 8, 2011), we have received new data that indicates the unsafe condition would not be adequately addressed by the proposed action. Subsequently, we are considering issuing new rulemaking that positively addresses the unsafe condition identified in the NPRM and eliminates the need for the actions proposed in the NPRM. VerDate Mar<15>2010 Regulatory Impact We propose to adopt a new airworthiness directive (AD) for certain Eurocopter France (Eurocopter) Model AS332C, AS332L, AS332L1, AS332L2, and EC225LP helicopters to require inspecting for the presence of blind holes in the tail gearbox (TGB) attachment fittings, and, if they are missing, installing an additional washer under the head of the attachment bolt until the attachment fitting is replaced with an airworthy attachment fitting. This proposed AD was prompted by the discovery of interference between the TGB aft attachment bolt and the structure fitting, caused by a manufacturing anomaly that omitted the blind hole required for proper fit of the attachment bolt. This condition, if not detected and corrected, could result in insufficient tightening of the TGB SUMMARY: PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 casing, damage to the TGB attachment, cracking under the attachment bolt, and loss of the TGB, resulting in loss of control of the helicopter. DATES: We must receive comments on this proposed AD by June 21, 2013. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this proposed AD, contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232– 0323; fax (972) 641–3775; or at http:// www.eurocopter.com/techpub. 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: Gary Roach, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222–5110; email gary.b.roach@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this E:\FR\FM\22APP1.SGM 22APP1 Federal Register / Vol. 78, No. 77 / Monday, April 22, 2013 / Proposed Rules document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this proposal in light of the comments we receive. tkelley on DSK3SPTVN1PROD with PROPOSALS Discussion ´ ´ The Direction Generale de L’Aviation Civile France (DGAC), the aviation authority for France, has issued DGAC AD No. F–2007–027, dated January 2, 2008 (F–2007–027), to correct an unsafe condition for certain Eurocopter AS332 series and EC225 LP helicopters. The DGAC advises that during a scheduled maintenance check, a helicopter was discovered to have interference between the threaded section of the aft attachment bolt and the structure fitting. The interference is because of a manufacturing anomaly in the fittings that omitted the blind hole for bolt clearance in the structure fitting. Interference from this missing blind hole does not permit correct axial tightening of the TGB casing, even if the correct torque load is applied to the attachment bolt. Insufficient tightening of the bolt can damage the TGB attachment and initiate a crack under the head of the attachment bolt. This condition, if not corrected, could result in loss of the TGB and subsequent loss of control of the helicopter. FAA’s Determination These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, DGAC, which is the production oversight authority for France, has notified us of the unsafe condition described in its AD. We are proposing this AD because we evaluated all known relevant information and determined that an unsafe condition exists and is likely to exist or develop on other products of these same type designs. VerDate Mar<15>2010 16:36 Apr 19, 2013 Jkt 229001 Related Service Information Eurocopter has issued one Emergency Alert Service Bulletin (EASB), Revision 1, dated January 4, 2008, with four different numbers. EASB No. 53.01.58 is for the Model AS332 series helicopters; EASB No. 53.00.58 is for the Model AS532 series helicopters, which are not FAA type certificated; EASB No. 53A012 is for the Model EC225LP helicopter; and EASB No. 53A011 is for the Model EC 725AP helicopter, which is not FAA type certificated. The EASB specifies inspecting the forward and aft attachment fittings for proper depth of the bolt holes. If the bolt holes are less than the minimum depth, the EASB specifies checking the condition of the bolt. If there are no signs of chafing or contact, the EASB calls for adding an additional washer to the bolt and reinstalling the bolt in the TGB attachment fitting. If there are signs of chafing or contact, the EASB requires replacing the bolt with an airworthy bolt and two washers. The DGAC classified this EASB as mandatory and issued F– 2007–027 to ensure the continued airworthiness of these helicopters. Proposed AD Requirements This proposed AD would require, within 50 hours time-in-service, inspecting the TGB aft and forward attachment fittings for the presence of a blind hole and measuring the depth. If the measurement is equal to or greater than 81 mm, no action would be necessary. If the measurement is less than 81 mm, the proposed AD would require inspecting the attachment bolts for chafing or contact marks. If there is no chafing or marks, the proposed AD would require reinstalling each bolt with an additional washer. If there is chafing or contact marks, the proposed AD would require replacing each bolt with an airworthy bolt and an additional washer. Costs of Compliance We estimate that this proposed AD would affect six helicopters of U.S. registry. Based on an average estimated labor cost of $85 per work-hour, we estimate the following costs: • Inspecting the TGB for the presence of a blind hole would require 0.50 workhour for a labor cost of about $43. No parts would be needed, so the cost would total $43 per helicopter, or $258 for the fleet. • Replacing bolts and adding a second washer if needed would require 0.50 work-hour for a labor cost of about $43. Parts would cost about $200 for three replacement bolts and the washers for a total cost of $243 per helicopter. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 23687 • Replacing the TGB attachment fitting with an airworthy fitting would require 40 work-hours for a labor cost of $3,400. Parts would cost about $1,921 for a total cost of $5,321 per helicopter. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, E:\FR\FM\22APP1.SGM 22APP1 23688 Federal Register / Vol. 78, No. 77 / Monday, April 22, 2013 / Proposed Rules the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new Airworthiness Directive (AD): ■ Eurocopter France Helicopters: Docket No. FAA–2013–0353; Directorate Identifier 2008–SW–029–AD. (a) Applicability This AD applies to Eurocopter France (Eurocopter) models AS332C, AS332L, AS332L1, AS332L2, and EC225LP helicopters, serial numbers (S/N) up to and including 2680 and S/N 9000 through 9009, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as interference between the tail gearbox (TGB) attachment bolt and the structure fitting. This condition could result in insufficient tightening of the TGB casing, damage to the TGB attachment, cracking under the attachment bolt, loss of the TGB and consequently, loss of helicopter control. tkelley on DSK3SPTVN1PROD with PROPOSALS (c) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (d) Required Actions Within 50 hours time-in-service (TIS): (1) Inspect the TGB aft attachment fitting to measure the dimension for a blind hole as follows: (i) Remove the TGB attachment bolt (c) but retain washer (d) as depicted in Detail A, Figure 1, of Eurocopter Emergency Alert Service Bulletin (EASB) No. 53.01.58 and EASB No. 53A012, both Revision 1, and both dated January 4, 2008. (ii) Use a depth gauge to measure dimension ‘‘x’’ between the top face of the washer (d) and the bottom of aft fitting (a) as depicted in Detail A, Figure 1, of the EASB. (2) If the measurement is equal to or greater than 81 mm, then the blind hole is present. Install the TGB attachment bolt (c) with its washer (d) as depicted in Detail A, Figure 1, of the EASB. Lock with lockwire. (3) If the measurement is less than 81 mm, then the blind hole is missing. Inspect the end of the threaded section of bolt (c) for chafing or a contact mark, as depicted in Area 1, Figure 1, of the EASB. (i) If there is no chafing and no contact marks, install bolt (c) with washer (d) and additional washer (2) as depicted in Detail B, Figure 1, of the EASB. (ii) If there is chafing or a contact mark, replace the TGB attachment bolt (c) with an airworthy bolt and install with washer (d) and additional washer (2) as depicted in VerDate Mar<15>2010 16:36 Apr 19, 2013 Jkt 229001 Detail B, Figure 1, of the EASB. Lock with lockwire. (iii) Within the next 825 hours TIS, replace the TGB aft attachment fitting with an airworthy attachment fitting. (4) Inspect the right and left attachment points of the TGB forward attachment to measure the dimension for a blind hole, as follows: (i) Remove both TGB attachment bolts (c) but retain washers (d), as depicted in Detail A, Figure 2, of the EASB. (ii) Use a depth gauge to measure dimension ‘‘x’’ between the top face of washer (d) and the bottom of forward fitting (b) at the right and left attachment points, as depicted in Detail A, Figure 2, of the EASB. (5) If both measurements are equal to or greater than 81 mm, then the blind hole is present. Install TGB attachment bolt (c) with its washer (d), as depicted in Detail A, Figure 2, of the EASB. Lock with lockwire. (6) If one or both measurements are less than 81 mm, then the blind hole is missing. Inspect the end of the threaded section of each bolt (c) for chafing or a contact mark, as depicted in Area 1, Figure 2 of the EASB. (i) If there is no chafing and no contact marks, for each attachment point, install bolt (c) with washer (d) and additional washer (2), as depicted in Detail B, Figure 2, of the EASB. (ii) If there is chafing or a contact mark, replace each the TGB attachment bolt (c) with an airworthy bolt and install bolt (1) with washer (d) and additional washer (2), as depicted in Detail B, Figure 2, of the EASB. Lock with lockwire. (iii) Within the next 825 hours TIS, replace the TGB forward attachment fitting with an airworthy attachment fitting. (e) Alternative Methods of Compliance (AMOC) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Gary Roach, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222–5110; email gary.b.roach@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (f) Additional Information The subject of this AD is addressed in the ´ ´ Direction Generale de L’Aviation Civile France AD No F–2007–027, dated January 2, 2008. (g) Subject Joint Aircraft Service Component (JASC) Code: 6520, Tail Rotor Gearbox. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Issued in Fort Worth, Texas, on April 11, 2013. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2013–09414 Filed 4–19–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0349; Directorate Identifier 2012–SW–058–AD] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Inc. Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Bell Helicopter Textron Canada Inc. (BHT) Model 206A, 206B, and 206L helicopters. This proposed AD would require replacing certain part-numbered engine auto-relight kit control boxes. This proposed AD is prompted by a design review that revealed the control box chipset did not meet the required temperature range requirements, which could cause the control box to malfunction, disabling the engine autorelight system. This condition could result in increased pilot workload during a power loss emergency and subsequent loss of control of the aircraft. DATES: We must receive comments on this proposed AD by June 21, 2013. 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. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the E:\FR\FM\22APP1.SGM 22APP1

Agencies

[Federal Register Volume 78, Number 77 (Monday, April 22, 2013)]
[Proposed Rules]
[Pages 23686-23688]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-09414]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0353; Directorate Identifier 2008-SW-029-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Eurocopter France (Eurocopter) Model AS332C, AS332L, AS332L1, 
AS332L2, and EC225LP helicopters to require inspecting for the presence 
of blind holes in the tail gearbox (TGB) attachment fittings, and, if 
they are missing, installing an additional washer under the head of the 
attachment bolt until the attachment fitting is replaced with an 
airworthy attachment fitting. This proposed AD was prompted by the 
discovery of interference between the TGB aft attachment bolt and the 
structure fitting, caused by a manufacturing anomaly that omitted the 
blind hole required for proper fit of the attachment bolt. This 
condition, if not detected and corrected, could result in insufficient 
tightening of the TGB casing, damage to the TGB attachment, cracking 
under the attachment bolt, and loss of the TGB, resulting in loss of 
control of the helicopter.

DATES: We must receive comments on this proposed AD by June 21, 2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the economic 
evaluation, any comments received, and other information. The street 
address for the Docket Operations Office (telephone 800-647-5527) is in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.
    For service information identified in this proposed AD, contact 
American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; 
or at http://www.eurocopter.com/techpub. 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: Gary Roach, Aviation Safety Engineer, 
Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham 
Blvd., Fort Worth, TX 76137; telephone (817) 222-5110; email 
gary.b.roach@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to participate in this rulemaking by submitting 
written comments, data, or views. We also invite comments relating to 
the economic, environmental, energy, or federalism impacts that might 
result from adopting the proposals in this

[[Page 23687]]

document. The most helpful comments reference a specific portion of the 
proposal, explain the reason for any recommended change, and include 
supporting data. To ensure the docket does not contain duplicate 
comments, commenters should send only one copy of written comments, or 
if comments are filed electronically, commenters should submit only one 
time.
    We will file in the docket all comments that we receive, as well as 
a report summarizing each substantive public contact with FAA personnel 
concerning this proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    The Direction G[eacute]n[eacute]rale de L'Aviation Civile France 
(DGAC), the aviation authority for France, has issued DGAC AD No. F-
2007-027, dated January 2, 2008 (F-2007-027), to correct an unsafe 
condition for certain Eurocopter AS332 series and EC225 LP helicopters. 
The DGAC advises that during a scheduled maintenance check, a 
helicopter was discovered to have interference between the threaded 
section of the aft attachment bolt and the structure fitting. The 
interference is because of a manufacturing anomaly in the fittings that 
omitted the blind hole for bolt clearance in the structure fitting. 
Interference from this missing blind hole does not permit correct axial 
tightening of the TGB casing, even if the correct torque load is 
applied to the attachment bolt. Insufficient tightening of the bolt can 
damage the TGB attachment and initiate a crack under the head of the 
attachment bolt. This condition, if not corrected, could result in loss 
of the TGB and subsequent loss of control of the helicopter.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
France and are approved for operation in the United States. Pursuant to 
our bilateral agreement with France, DGAC, which is the production 
oversight authority for France, has notified us of the unsafe condition 
described in its AD. We are proposing this AD because we evaluated all 
known relevant information and determined that an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Related Service Information

    Eurocopter has issued one Emergency Alert Service Bulletin (EASB), 
Revision 1, dated January 4, 2008, with four different numbers. EASB 
No. 53.01.58 is for the Model AS332 series helicopters; EASB No. 
53.00.58 is for the Model AS532 series helicopters, which are not FAA 
type certificated; EASB No. 53A012 is for the Model EC225LP helicopter; 
and EASB No. 53A011 is for the Model EC 725AP helicopter, which is not 
FAA type certificated. The EASB specifies inspecting the forward and 
aft attachment fittings for proper depth of the bolt holes. If the bolt 
holes are less than the minimum depth, the EASB specifies checking the 
condition of the bolt. If there are no signs of chafing or contact, the 
EASB calls for adding an additional washer to the bolt and reinstalling 
the bolt in the TGB attachment fitting. If there are signs of chafing 
or contact, the EASB requires replacing the bolt with an airworthy bolt 
and two washers. The DGAC classified this EASB as mandatory and issued 
F-2007-027 to ensure the continued airworthiness of these helicopters.

Proposed AD Requirements

    This proposed AD would require, within 50 hours time-in-service, 
inspecting the TGB aft and forward attachment fittings for the presence 
of a blind hole and measuring the depth. If the measurement is equal to 
or greater than 81 mm, no action would be necessary. If the measurement 
is less than 81 mm, the proposed AD would require inspecting the 
attachment bolts for chafing or contact marks. If there is no chafing 
or marks, the proposed AD would require reinstalling each bolt with an 
additional washer. If there is chafing or contact marks, the proposed 
AD would require replacing each bolt with an airworthy bolt and an 
additional washer.

Costs of Compliance

    We estimate that this proposed AD would affect six helicopters of 
U.S. registry. Based on an average estimated labor cost of $85 per 
work-hour, we estimate the following costs:
     Inspecting the TGB for the presence of a blind hole would 
require 0.50 work-hour for a labor cost of about $43. No parts would be 
needed, so the cost would total $43 per helicopter, or $258 for the 
fleet.
     Replacing bolts and adding a second washer if needed would 
require 0.50 work-hour for a labor cost of about $43. Parts would cost 
about $200 for three replacement bolts and the washers for a total cost 
of $243 per helicopter.
     Replacing the TGB attachment fitting with an airworthy 
fitting would require 40 work-hours for a labor cost of $3,400. Parts 
would cost about $1,921 for a total cost of $5,321 per helicopter.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed, I certify this proposed regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska to the extent that 
it justifies making a regulatory distinction; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator,

[[Page 23688]]

the FAA proposes to amend 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. The FAA amends Sec.  39.13 by adding the following new Airworthiness 
Directive (AD):

Eurocopter France Helicopters: Docket No. FAA-2013-0353; Directorate 
Identifier 2008-SW-029-AD.

(a) Applicability

    This AD applies to Eurocopter France (Eurocopter) models AS332C, 
AS332L, AS332L1, AS332L2, and EC225LP helicopters, serial numbers 
(S/N) up to and including 2680 and S/N 9000 through 9009, 
certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as interference between the 
tail gearbox (TGB) attachment bolt and the structure fitting. This 
condition could result in insufficient tightening of the TGB casing, 
damage to the TGB attachment, cracking under the attachment bolt, 
loss of the TGB and consequently, loss of helicopter control.

(c) Compliance

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

(d) Required Actions

    Within 50 hours time-in-service (TIS):
    (1) Inspect the TGB aft attachment fitting to measure the 
dimension for a blind hole as follows:
    (i) Remove the TGB attachment bolt (c) but retain washer (d) as 
depicted in Detail A, Figure 1, of Eurocopter Emergency Alert 
Service Bulletin (EASB) No. 53.01.58 and EASB No. 53A012, both 
Revision 1, and both dated January 4, 2008.
    (ii) Use a depth gauge to measure dimension ``x'' between the 
top face of the washer (d) and the bottom of aft fitting (a) as 
depicted in Detail A, Figure 1, of the EASB.
    (2) If the measurement is equal to or greater than 81 mm, then 
the blind hole is present. Install the TGB attachment bolt (c) with 
its washer (d) as depicted in Detail A, Figure 1, of the EASB. Lock 
with lockwire.
    (3) If the measurement is less than 81 mm, then the blind hole 
is missing. Inspect the end of the threaded section of bolt (c) for 
chafing or a contact mark, as depicted in Area 1, Figure 1, of the 
EASB.
    (i) If there is no chafing and no contact marks, install bolt 
(c) with washer (d) and additional washer (2) as depicted in Detail 
B, Figure 1, of the EASB.
    (ii) If there is chafing or a contact mark, replace the TGB 
attachment bolt (c) with an airworthy bolt and install with washer 
(d) and additional washer (2) as depicted in Detail B, Figure 1, of 
the EASB. Lock with lockwire.
    (iii) Within the next 825 hours TIS, replace the TGB aft 
attachment fitting with an airworthy attachment fitting.
    (4) Inspect the right and left attachment points of the TGB 
forward attachment to measure the dimension for a blind hole, as 
follows:
    (i) Remove both TGB attachment bolts (c) but retain washers (d), 
as depicted in Detail A, Figure 2, of the EASB.
    (ii) Use a depth gauge to measure dimension ``x'' between the 
top face of washer (d) and the bottom of forward fitting (b) at the 
right and left attachment points, as depicted in Detail A, Figure 2, 
of the EASB.
    (5) If both measurements are equal to or greater than 81 mm, 
then the blind hole is present. Install TGB attachment bolt (c) with 
its washer (d), as depicted in Detail A, Figure 2, of the EASB. Lock 
with lockwire.
    (6) If one or both measurements are less than 81 mm, then the 
blind hole is missing. Inspect the end of the threaded section of 
each bolt (c) for chafing or a contact mark, as depicted in Area 1, 
Figure 2 of the EASB.
    (i) If there is no chafing and no contact marks, for each 
attachment point, install bolt (c) with washer (d) and additional 
washer (2), as depicted in Detail B, Figure 2, of the EASB.
    (ii) If there is chafing or a contact mark, replace each the TGB 
attachment bolt (c) with an airworthy bolt and install bolt (1) with 
washer (d) and additional washer (2), as depicted in Detail B, 
Figure 2, of the EASB. Lock with lockwire.
    (iii) Within the next 825 hours TIS, replace the TGB forward 
attachment fitting with an airworthy attachment fitting.

 (e) Alternative Methods of Compliance (AMOC)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Gary Roach, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222-5110; 
email gary.b.roach@faa.gov.
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest that you 
notify your principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office or 
certificate holding district office before operating any aircraft 
complying with this AD through an AMOC.

(f) Additional Information

    The subject of this AD is addressed in the Direction 
G[eacute]n[eacute]rale de L'Aviation Civile France AD No F-2007-027, 
dated January 2, 2008.

(g) Subject

    Joint Aircraft Service Component (JASC) Code: 6520, Tail Rotor 
Gearbox.

    Issued in Fort Worth, Texas, on April 11, 2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-09414 Filed 4-19-13; 8:45 am]
BILLING CODE 4910-13-P