Airworthiness Directives; MD Helicopters Inc., Helicopters, 53028-53030 [2015-21680]

Download as PDF 53028 Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Proposed Rules asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (C) Record measurement M1 indicated on the caliper gage on the component history card or equivalent record. (ii) On the tail rotor hub (TRH) side: (A) Remove the fairing and perform a measurement ‘‘M2’’ using a caliper gage between the flat face of the center plate (item c in the photograph in the Accomplishment Instructions under paragraph 3.B.4.b.(2) of ASB AS365–05.00.61, SA336–05.41, or EC155–05A022) and the face of the inner web (item ad in the photograph in the Accomplishment Instructions under paragraph 3.B.4.b.(2) of ASB AS365– 05.00.61, SA336–05.41, or EC155–05A022) of the rotor hub on which the inner bearings of the TRH blades are installed. Position the caliper gage flat across the opening of the pitch change spider on R2 and R3 as shown in the right photograph in the Accomplishment Instructions under paragraph 3.B.4.b.(2) of ASB AS365– 05.00.61, SA336–05.41, or EC155–05A022. (B) Record measurement M2 indicated on the caliper gage on the component history card or equivalent record. (C) Calculate a measurement ‘‘M3’’ by adding measurements M1 and M2. (D) Calculate the difference between measurement ‘‘M0’’ indicated on the TGB component history card or equivalent record and M3. (1) If the difference between measurement M0 and M3 is less than 0.5 mm (0.02 inch), perform an additional inspection for play in the bearing of the TGB control shaft and rod assembly by following the Accomplishment Instructions, paragraph 3.B.6., of ASB AS365–05.00.61, SA366–05.41, or EC155– 05A022. If there is no axial play at the TRH pitch change spider, record value M3 on the component history card or equivalent record. If there is axial play at the TRH pitch change spider, replace the bearing with an airworthy bearing and perform a new reference measurement by following the requirements of paragraph (f)(6) of this AD. (2) If the difference between the measurements is equal to or greater than 0.5 mm (0.02 inch), replace the bearing with an airworthy bearing and perform a new reference measurement by following the requirements of paragraph (f)(6) of this AD. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Wilbanks, Aviation Safety Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, Texas 76177; telephone (817) 222–5110; email 9-ASW-FTW-AMOC-Requests@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) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD VerDate Sep<11>2014 18:00 Sep 01, 2015 Jkt 235001 No. 2012–0170R2, dated June 20, 2014. You may view the EASA AD on the internet at http://www.regulations.gov in Docket No. FAA–2015–3657. (i) Subject Joint Aircraft Service Component (JASC) Code: 6520 Tail Rotor Gearbox. Issued in Fort Worth, Texas, on August 21, 2015. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2015–21689 Filed 9–1–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–3659; Directorate Identifier 2014–SW–050–AD] RIN 2120–AA64 Airworthiness Directives; MD Helicopters Inc., Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for MD Helicopters Inc. (MDHI) Model 369A, 369D, 369E, 369FF, 369HE, 369HM, 369HS, 500N, and 600N helicopters with a certain part-numbered main rotor blade attach pin (pin) installed. This proposed AD would require ensuring the life limit of the pin as listed in the Airworthiness Limitations section of aircraft maintenance records and Instructions for Continued Airworthiness (ICA). If the hours timein-service (TIS) of a pin is unknown, or if a pin has exceeded its life limit, this proposed AD would require removing the affected pin from service. This proposed AD is prompted by a report from an operator who purchased pins that did not have life limit documentation. The proposed actions are intended to document the life limit to prevent a pin remaining in service beyond its fatigue life, which could result in failure of a pin, failure of a main rotor blade, and subsequent loss of control of the helicopter. DATES: We must receive comments on this proposed AD by November 2, 2015. 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. SUMMARY: PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 • 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 Aerometals, 3920 Sandstone Dr., El Dorado Hills, CA 95762, telephone (916) 939–6888, fax (916) 939–6555, www.aerometals.aero. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. FOR FURTHER INFORMATION CONTACT: Galib Abumeri, Aviation Safety Engineer, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, FAA, 3960 Paramount Blvd., Lakewood, California 90712; telephone (562) 627–5324; email Galib.Abumeri@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive E:\FR\FM\02SEP1.SGM 02SEP1 Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Proposed Rules 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. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS Discussion We propose to adopt a new AD for MDHI Model 369A, 369D, 369E, 369FF, 369HE, 369HM, 369HS, 500N, and 600N helicopters with a pin part-number (P/ N) 369X1004–5 installed. This proposed AD would require determining the number of hours TIS of each pin and whether the aircraft maintenance records contain a pin life limit. If the hours TIS are unknown, this proposed AD would require removing the pin from service. If the aircraft maintenance records do not contain a pin life limit, this proposed AD would require revising the records and establishing a life limit of 5,760 hours if the pin is installed on a Model 369A, 369HE, 369HM, or 369HS helicopter, or 7,600 hours if the pin is installed on a Model 369D, 369E, 369FF, 500N, or 600N helicopter. This proposed AD would also require revising the records to add a statement that if a pin is interchanged between different model helicopters, then its life limit must be restricted to the lower life limit even if it was originally installed on a helicopter model with a higher life limit. Lastly, this proposed AD would prohibit installing a pin on any helicopter before these proposed requirements have been accomplished. Aerometals produces pin P/N 369X1004–5 under a parts manufacturer approval as a replacement pin for MDHI P/N 369A1004–5. This proposed AD is prompted by a report from an operator who purchased Aerometals’ pins P/N 369X1004–5 without life limit documentation. The FAA inadvertently approved the pins without a life limit in the Airworthiness Limitations section and without a restriction for parts that are interchanged between models with different life limits. A total of 5,133 affected pins were sold by Aerometals without any indication that the parts were life-limited. The proposed actions are intended to correct the failure of these parts to have a documented life limit to prevent a pin remaining in service beyond its fatigue life, which could result in failure of a pin, failure of a main rotor blade, and subsequent loss of control of the helicopter. VerDate Sep<11>2014 18:00 Sep 01, 2015 Jkt 235001 FAA’s Determination 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 Aerometals has issued Aero-ICA–1001 Supplemental Instructions for Continued Airworthiness, Revision NC, dated May 22, 2014, and Service Bulletin Aero-SB–1103, dated July 2, 2014. The service bulletin specifies determining whether the helicopter has pins P/N 369X1004–5 installed and then reviewing the aircraft maintenance records to determine if the pins have a life limit identified. If the life limit is not the same as that listed in the ICA, the service bulletin specifies revising the life limit in the maintenance records. The service bulletin states that the pins were approved by the FAA as Parts Manufacturer Approval direct replacement parts with the same life limits as the parts they replace. However, they were sold without an FAA-approved supplemental ICA containing an Airworthiness Limitations Section specifically assigning these life limits to the pins. Proposed AD Requirements This proposed AD would require, within 100 hours TIS or during the next annual inspection, whichever comes first: ° Reviewing the maintenance records and determining the hours TIS of each pin and whether there is a pin life limit listed in the Airworthiness Limitations Section of the applicable maintenance manual or ICA. If the hours TIS on a pin are unknown, the proposed AD would require removing the pin from service. ° For Model 369A, 369HE, 369HM, and 369HS helicopters, if there is no pin life limit, establishing a new life limit of 5,760 hours TIS and removing any pin from service that has 5,760 or more hours TIS. ° For Model 369D, 369E, 369FF, 500N and 600N helicopters, if there is no pin life limit, establishing a new life limit of 7,600 hours TIS and removing any pin from service that has 7,600 or more hours TIS. ° For all model helicopters, establishing a requirement that if a pin is interchanged between model helicopters with different life limits, the life limit of the pin must be restricted to the lowest life limit. This proposed AD would also prohibit installing a pin P/N 369X1004– 5 on any helicopter until the PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 53029 requirements of the AD have been accomplished. Costs of Compliance We estimate that this proposed AD would affect 118 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. Labor costs are estimated at $85 per hour. We estimate l/2 work hour to inspect and record any update for a total of $42.50 per helicopter and $5,015 for the U.S. fleet. If required, we estimate 1 work hour per helicopter to replace 10 pins because each blade has 2 pins and each helicopter has 5 blades. Required parts are $445 for each pin. Based on these estimates, it would cost $4,535 per helicopter to replace 10 pins if the pins have exceeded their life limit. 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 E:\FR\FM\02SEP1.SGM 02SEP1 53030 Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Proposed Rules 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by Reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ MD Helicopters Inc.: Docket No. FAA–2015– 3659; Directorate Identifier 2014–SW– 050–AD. (a) Applicability This AD applies to Model 369A, 369D, 369E, 369FF, 369HE, 369HM, 369HS, 500N, and 600N helicopters with an Aerometals main rotor blade attach pin (pin) part number (P/N) 369X1004–5 installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a pin remaining in service beyond its fatigue life. This condition could result in failure of a pin, loss of a main rotor blade, and subsequent loss of control of the helicopter. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (c) Comments Due Date We must receive comments by November 2, 2015. (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 (1) Within 100 hours time-in-service (TIS) or during the next annual inspection, whichever occurs first: (i) Review the maintenance records and determine the hours TIS of each pin VerDate Sep<11>2014 18:00 Sep 01, 2015 Jkt 235001 P/N 369X1004–5 and whether there is a pin life limit listed in the Airworthiness Limitations Section of the applicable maintenance manual or Instructions for Continued Airworthiness (ICA). If the hours TIS on a pin is unknown, remove the pin from service. (ii) For Model 369A, 369HE, 369HM, and 369HS helicopters, if there is no pin life limit, establish a new life limit of 5,760 hours TIS for each pin P/N 369X1004–5 by making pen-and-ink changes or by inserting a copy of this AD into the Airworthiness Limitations Section of the maintenance manual or the ICA. Remove from service any pin that has 5,760 or more hours TIS. (iii) For Model 369D, 369E, 369FF, 500N, and 600N helicopters, if there is no pin life limit, establish a new life limit of 7,600 hours TIS for each pin P/ N 369X1004–5 by making pen-and-ink changes or by inserting a copy of this AD into the Airworthiness Limitations Section of the maintenance manual or the ICA. Remove from service any pin that has 7,600 or more hours TIS. (iv) For all model helicopters, add the following statement to the Airworthiness Limitations Section of the maintenance manual or the ICA by making pen-and-ink changes or by inserting a copy of this AD: If interchanged between different model helicopters, the life limit of pin P/N 369X1004–5 must be restricted to the lowest life limit indicated for the helicopter models and serial numbers affected. (2) Do not install a pin P/N 369X1004–5 on any helicopter before the requirements of this AD have been accomplished. (f) Alternative Methods of Compliance (AMOC) (1) The Manager, Los Angeles Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Galib Abumeri, Aviation Safety Engineer, Transport Airplane Directorate, FAA, 3960 Paramount Blvd., Lakewood, California 90712; telephone (562) 627–5324 or email at 9ANM-LAACO-AMOCREQUESTS@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. PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 (g) Additional Information Aerometals Service Bulletin Aero– SB–1103, dated July 2, 2014, and Aerometals Aero–ICA–101 Supplemental Instructions for Continued Airworthiness, Revision NC, dated May 22, 2014, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Aerometals, 3920 Sandstone Dr., El Dorado Hills, CA 95762, telephone (916) 939–6888, fax (916) 939–6555, www.aerometals.aero. You may review a copy of information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. (h) Subject Joint Aircraft Service Component (JASC) Code: 6210 Main Rotor Blades. Issued in Fort Worth, Texas, on August 21, 2015. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2015–21680 Filed 9–1–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–3658; Directorate Identifier 2014–SW–039–AD] RIN 2120–AA64 Airworthiness Directives; MD Helicopters Inc. (MDHI) Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain MDHI Model 369A (Army OH–6A), 369H, 369HE, 369HM, 369HS, 369D, 369E, 369F, 369FF, and 500N helicopters. This proposed AD would require inspecting the auxiliary fuel pump (fuel pump) wire routing in the left-hand fuel cell and corrective action, if necessary. This proposed AD would also require installing a warning decal on the left-hand fuel cell access cover. This proposed AD is prompted by accidents resulting from incorrectly positioned fuel pump wiring within the fuel tank interfering with the operation of the fuel quantity sensor float, which caused an erroneous fuel quantity SUMMARY: E:\FR\FM\02SEP1.SGM 02SEP1

Agencies

[Federal Register Volume 80, Number 170 (Wednesday, September 2, 2015)]
[Proposed Rules]
[Pages 53028-53030]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-21680]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3659; Directorate Identifier 2014-SW-050-AD]
RIN 2120-AA64


Airworthiness Directives; MD Helicopters Inc., Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for MD 
Helicopters Inc. (MDHI) Model 369A, 369D, 369E, 369FF, 369HE, 369HM, 
369HS, 500N, and 600N helicopters with a certain part-numbered main 
rotor blade attach pin (pin) installed. This proposed AD would require 
ensuring the life limit of the pin as listed in the Airworthiness 
Limitations section of aircraft maintenance records and Instructions 
for Continued Airworthiness (ICA). If the hours time-in-service (TIS) 
of a pin is unknown, or if a pin has exceeded its life limit, this 
proposed AD would require removing the affected pin from service. This 
proposed AD is prompted by a report from an operator who purchased pins 
that did not have life limit documentation. The proposed actions are 
intended to document the life limit to prevent a pin remaining in 
service beyond its fatigue life, which could result in failure of a 
pin, failure of a main rotor blade, and subsequent loss of control of 
the helicopter.

DATES: We must receive comments on this proposed AD by November 2, 
2015.

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 
Aerometals, 3920 Sandstone Dr., El Dorado Hills, CA 95762, telephone 
(916) 939-6888, fax (916) 939-6555, www.aerometals.aero. You may review 
the referenced service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort 
Worth, TX 76177.

FOR FURTHER INFORMATION CONTACT: Galib Abumeri, Aviation Safety 
Engineer, Los Angeles Aircraft Certification Office, Transport Airplane 
Directorate, FAA, 3960 Paramount Blvd., Lakewood, California 90712; 
telephone (562) 627-5324; email Galib.Abumeri@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

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

[[Page 53029]]

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

    We propose to adopt a new AD for MDHI Model 369A, 369D, 369E, 
369FF, 369HE, 369HM, 369HS, 500N, and 600N helicopters with a pin part-
number (P/N) 369X1004-5 installed. This proposed AD would require 
determining the number of hours TIS of each pin and whether the 
aircraft maintenance records contain a pin life limit. If the hours TIS 
are unknown, this proposed AD would require removing the pin from 
service. If the aircraft maintenance records do not contain a pin life 
limit, this proposed AD would require revising the records and 
establishing a life limit of 5,760 hours if the pin is installed on a 
Model 369A, 369HE, 369HM, or 369HS helicopter, or 7,600 hours if the 
pin is installed on a Model 369D, 369E, 369FF, 500N, or 600N 
helicopter. This proposed AD would also require revising the records to 
add a statement that if a pin is interchanged between different model 
helicopters, then its life limit must be restricted to the lower life 
limit even if it was originally installed on a helicopter model with a 
higher life limit. Lastly, this proposed AD would prohibit installing a 
pin on any helicopter before these proposed requirements have been 
accomplished.
    Aerometals produces pin P/N 369X1004-5 under a parts manufacturer 
approval as a replacement pin for MDHI P/N 369A1004-5. This proposed AD 
is prompted by a report from an operator who purchased Aerometals' pins 
P/N 369X1004-5 without life limit documentation. The FAA inadvertently 
approved the pins without a life limit in the Airworthiness Limitations 
section and without a restriction for parts that are interchanged 
between models with different life limits. A total of 5,133 affected 
pins were sold by Aerometals without any indication that the parts were 
life-limited. The proposed actions are intended to correct the failure 
of these parts to have a documented life limit to prevent a pin 
remaining in service beyond its fatigue life, which could result in 
failure of a pin, failure of a main rotor blade, and subsequent loss of 
control of the helicopter.

FAA's Determination

    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

    Aerometals has issued Aero-ICA-1001 Supplemental Instructions for 
Continued Airworthiness, Revision NC, dated May 22, 2014, and Service 
Bulletin Aero-SB-1103, dated July 2, 2014. The service bulletin 
specifies determining whether the helicopter has pins P/N 369X1004-5 
installed and then reviewing the aircraft maintenance records to 
determine if the pins have a life limit identified. If the life limit 
is not the same as that listed in the ICA, the service bulletin 
specifies revising the life limit in the maintenance records. The 
service bulletin states that the pins were approved by the FAA as Parts 
Manufacturer Approval direct replacement parts with the same life 
limits as the parts they replace. However, they were sold without an 
FAA-approved supplemental ICA containing an Airworthiness Limitations 
Section specifically assigning these life limits to the pins.

Proposed AD Requirements

    This proposed AD would require, within 100 hours TIS or during the 
next annual inspection, whichever comes first:
    [deg] Reviewing the maintenance records and determining the hours 
TIS of each pin and whether there is a pin life limit listed in the 
Airworthiness Limitations Section of the applicable maintenance manual 
or ICA. If the hours TIS on a pin are unknown, the proposed AD would 
require removing the pin from service.
    [deg] For Model 369A, 369HE, 369HM, and 369HS helicopters, if there 
is no pin life limit, establishing a new life limit of 5,760 hours TIS 
and removing any pin from service that has 5,760 or more hours TIS.
    [deg] For Model 369D, 369E, 369FF, 500N and 600N helicopters, if 
there is no pin life limit, establishing a new life limit of 7,600 
hours TIS and removing any pin from service that has 7,600 or more 
hours TIS.
    [deg] For all model helicopters, establishing a requirement that if 
a pin is interchanged between model helicopters with different life 
limits, the life limit of the pin must be restricted to the lowest life 
limit.
    This proposed AD would also prohibit installing a pin P/N 369X1004-
5 on any helicopter until the requirements of the AD have been 
accomplished.

Costs of Compliance

    We estimate that this proposed AD would affect 118 helicopters of 
U.S. Registry.
    We estimate that operators may incur the following costs in order 
to comply with this AD. Labor costs are estimated at $85 per hour. We 
estimate l/2 work hour to inspect and record any update for a total of 
$42.50 per helicopter and $5,015 for the U.S. fleet. If required, we 
estimate 1 work hour per helicopter to replace 10 pins because each 
blade has 2 pins and each helicopter has 5 blades. Required parts are 
$445 for each pin. Based on these estimates, it would cost $4,535 per 
helicopter to replace 10 pins if the pins have exceeded their life 
limit.

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

[[Page 53030]]

    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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):

MD Helicopters Inc.: Docket No. FAA-2015-3659; Directorate 
Identifier 2014-SW-050-AD.

(a) Applicability

    This AD applies to Model 369A, 369D, 369E, 369FF, 369HE, 369HM, 
369HS, 500N, and 600N helicopters with an Aerometals main rotor blade 
attach pin (pin) part number (P/N) 369X1004-5 installed, certificated 
in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a pin remaining in service 
beyond its fatigue life. This condition could result in failure of a 
pin, loss of a main rotor blade, and subsequent loss of control of the 
helicopter.

(c) Comments Due Date

    We must receive comments by November 2, 2015.

(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

    (1) Within 100 hours time-in-service (TIS) or during the next 
annual inspection, whichever occurs first:
    (i) Review the maintenance records and determine the hours TIS of 
each pin P/N 369X1004-5 and whether there is a pin life limit listed in 
the Airworthiness Limitations Section of the applicable maintenance 
manual or Instructions for Continued Airworthiness (ICA). If the hours 
TIS on a pin is unknown, remove the pin from service.
    (ii) For Model 369A, 369HE, 369HM, and 369HS helicopters, if there 
is no pin life limit, establish a new life limit of 5,760 hours TIS for 
each pin P/N 369X1004-5 by making pen-and-ink changes or by inserting a 
copy of this AD into the Airworthiness Limitations Section of the 
maintenance manual or the ICA. Remove from service any pin that has 
5,760 or more hours TIS.
    (iii) For Model 369D, 369E, 369FF, 500N, and 600N helicopters, if 
there is no pin life limit, establish a new life limit of 7,600 hours 
TIS for each pin P/N 369X1004-5 by making pen-and-ink changes or by 
inserting a copy of this AD into the Airworthiness Limitations Section 
of the maintenance manual or the ICA. Remove from service any pin that 
has 7,600 or more hours TIS.
    (iv) For all model helicopters, add the following statement to the 
Airworthiness Limitations Section of the maintenance manual or the ICA 
by making pen-and-ink changes or by inserting a copy of this AD: If 
interchanged between different model helicopters, the life limit of pin 
P/N 369X1004-5 must be restricted to the lowest life limit indicated 
for the helicopter models and serial numbers affected.
    (2) Do not install a pin P/N 369X1004-5 on any helicopter before 
the requirements of this AD have been accomplished.

(f) Alternative Methods of Compliance (AMOC)

    (1) The Manager, Los Angeles Aircraft Certification Office, FAA, 
may approve AMOCs for this AD. Send your proposal to: Galib Abumeri, 
Aviation Safety Engineer, Transport Airplane Directorate, FAA, 3960 
Paramount Blvd., Lakewood, California 90712; telephone (562) 627-5324 
or email at 9-ANM-LAACO-AMOC-REQUESTS@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.

(g) Additional Information

    Aerometals Service Bulletin Aero-SB-1103, dated July 2, 2014, and 
Aerometals Aero-ICA-101 Supplemental Instructions for Continued 
Airworthiness, Revision NC, dated May 22, 2014, which are not 
incorporated by reference, contain additional information about the 
subject of this AD. For service information identified in this AD, 
contact Aerometals, 3920 Sandstone Dr., El Dorado Hills, CA 95762, 
telephone (916) 939-6888, fax (916) 939-6555, www.aerometals.aero. You 
may review a copy of information at the FAA, Office of the Regional 
Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort 
Worth, TX 76177.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6210 Main Rotor 
Blades.


    Issued in Fort Worth, Texas, on August 21, 2015.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-21680 Filed 9-1-15; 8:45 am]
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