80 FR 53028 - Airworthiness Directives; MD Helicopters Inc., Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 170 (September 2, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 170 (September 2, 2015)
| Page Range | 53028-53030 | |
| FR Document | 2015-21680 |
[Federal Register Volume 80, Number 170 (Wednesday, September 2, 2015)] [Proposed Rules] [Pages 53028-53030] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-21680] ----------------------------------------------------------------------- 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 [email protected]. 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 [email protected]. (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] BILLING CODE 4910-13-P
![53028 Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Proposed Rules
(C) Record measurement M1 indicated on No. 2012–0170R2, dated June 20, 2014. You • Fax: 202–493–2251.
the caliper gage on the component history may view the EASA AD on the internet at • Mail: Send comments to the U.S.
card or equivalent record. http://www.regulations.gov in Docket No. Department of Transportation, Docket
(ii) On the tail rotor hub (TRH) side: FAA–2015–3657.
(A) Remove the fairing and perform a
Operations, M–30, West Building
measurement ‘‘M2’’ using a caliper gage (i) Subject Ground Floor, Room W12–140, 1200
between the flat face of the center plate (item Joint Aircraft Service Component (JASC) New Jersey Avenue SE., Washington,
c in the photograph in the Accomplishment Code: 6520 Tail Rotor Gearbox. DC 20590–0001.
Instructions under paragraph 3.B.4.b.(2) of Issued in Fort Worth, Texas, on August 21, • Hand Delivery: Deliver to the
ASB AS365–05.00.61, SA336–05.41, or 2015. ‘‘Mail’’ address between 9 a.m. and 5
EC155–05A022) and the face of the inner web p.m., Monday through Friday, except
(item ad in the photograph in the Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Federal holidays.
Accomplishment Instructions under
paragraph 3.B.4.b.(2) of ASB AS365– Directorate, Aircraft Certification Service. Examining the AD Docket
05.00.61, SA336–05.41, or EC155–05A022) of [FR Doc. 2015–21689 Filed 9–1–15; 8:45 am]
the rotor hub on which the inner bearings of You may examine the AD docket on
BILLING CODE 4910–13–P
the TRH blades are installed. Position the the Internet at http://
caliper gage flat across the opening of the www.regulations.gov or in person at the
pitch change spider on R2 and R3 as shown Docket Operations Office between 9
in the right photograph in the DEPARTMENT OF TRANSPORTATION
a.m. and 5 p.m., Monday through
Accomplishment Instructions under Friday, except Federal holidays. The AD
paragraph 3.B.4.b.(2) of ASB AS365– Federal Aviation Administration
05.00.61, SA336–05.41, or EC155–05A022.
docket contains this proposed AD, the
(B) Record measurement M2 indicated on 14 CFR Part 39 economic evaluation, any comments
the caliper gage on the component history received, and other information. The
card or equivalent record. [Docket No. FAA–2015–3659; Directorate street address for the Docket Operations
(C) Calculate a measurement ‘‘M3’’ by Identifier 2014–SW–050–AD] Office (telephone 800–647–5527) is in
adding measurements M1 and M2. RIN 2120–AA64 the ADDRESSES section. Comments will
(D) Calculate the difference between be available in the AD docket shortly
measurement ‘‘M0’’ indicated on the TGB Airworthiness Directives; MD after receipt.
component history card or equivalent record Helicopters Inc., Helicopters
and M3.
For service information identified in
(1) If the difference between measurement AGENCY: Federal Aviation this proposed AD, contact Aerometals,
M0 and M3 is less than 0.5 mm (0.02 inch), Administration (FAA), DOT. 3920 Sandstone Dr., El Dorado Hills, CA
perform an additional inspection for play in 95762, telephone (916) 939–6888, fax
ACTION: Notice of proposed rulemaking
the bearing of the TGB control shaft and rod (916) 939–6555, www.aerometals.aero.
assembly by following the Accomplishment (NPRM).
You may review the referenced service
Instructions, paragraph 3.B.6., of ASB SUMMARY: We propose to adopt a new information at the FAA, Office of the
AS365–05.00.61, SA366–05.41, or EC155– Regional Counsel, Southwest Region,
05A022. If there is no axial play at the TRH airworthiness directive (AD) for MD
pitch change spider, record value M3 on the Helicopters Inc. (MDHI) Model 369A, 10101 Hillwood Pkwy, Room 6N–321,
component history card or equivalent record. 369D, 369E, 369FF, 369HE, 369HM, Fort Worth, TX 76177.
If there is axial play at the TRH pitch change 369HS, 500N, and 600N helicopters FOR FURTHER INFORMATION CONTACT:
spider, replace the bearing with an airworthy with a certain part-numbered main rotor Galib Abumeri, Aviation Safety
bearing and perform a new reference blade attach pin (pin) installed. This Engineer, Los Angeles Aircraft
measurement by following the requirements proposed AD would require ensuring Certification Office, Transport Airplane
of paragraph (f)(6) of this AD. the life limit of the pin as listed in the
(2) If the difference between the
Directorate, FAA, 3960 Paramount
measurements is equal to or greater than 0.5 Airworthiness Limitations section of Blvd., Lakewood, California 90712;
mm (0.02 inch), replace the bearing with an aircraft maintenance records and telephone (562) 627–5324; email
airworthy bearing and perform a new Instructions for Continued Galib.Abumeri@faa.gov.
reference measurement by following the Airworthiness (ICA). If the hours time- SUPPLEMENTARY INFORMATION:
requirements of paragraph (f)(6) of this AD. in-service (TIS) of a pin is unknown, or
if a pin has exceeded its life limit, this Comments Invited
(g) Alternative Methods of Compliance
(AMOCs) proposed AD would require removing We invite you to participate in this
(1) The Manager, Safety Management
the affected pin from service. This rulemaking by submitting written
Group, FAA, may approve AMOCs for this proposed AD is prompted by a report comments, data, or views. We also
AD. Send your proposal to: Matt Wilbanks, from an operator who purchased pins invite comments relating to the
Aviation Safety Engineer, Rotorcraft that did not have life limit economic, environmental, energy, or
Certification Office, Rotorcraft Directorate, documentation. The proposed actions federalism impacts that might result
FAA, 10101 Hillwood Pkwy, Fort Worth, are intended to document the life limit from adopting the proposals in this
Texas 76177; telephone (817) 222–5110; to prevent a pin remaining in service document. The most helpful comments
email 9-ASW-FTW-AMOC-Requests@faa.gov. beyond its fatigue life, which could
(2) For operations conducted under a 14 reference a specific portion of the
CFR part 119 operating certificate or under
result in failure of a pin, failure of a proposal, explain the reason for any
main rotor blade, and subsequent loss of recommended change, and include
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or control of the helicopter. supporting data. To ensure the docket
lacking a principal inspector, the manager of DATES: We must receive comments on does not contain duplicate comments,
the local flight standards district office or this proposed AD by November 2, 2015. commenters should send only one copy
certificate holding district office before ADDRESSES: You may send comments by of written comments, or if comments are
operating any aircraft complying with this filed electronically, commenters should
AD through an AMOC.
any of the following methods:
• Federal eRulemaking Docket: Go to submit only one time.
(h) Additional Information http://www.regulations.gov. Follow the We will file in the docket all
The subject of this AD is addressed in online instructions for sending your comments that we receive, as well as a
European Aviation Safety Agency (EASA) AD comments electronically. report summarizing each substantive
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![53030 Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Proposed Rules
4. Will not have a significant P/N 369X1004–5 and whether there is a (g) Additional Information
economic impact, positive or negative, pin life limit listed in the Airworthiness Aerometals Service Bulletin Aero–
on a substantial number of small entities Limitations Section of the applicable SB–1103, dated July 2, 2014, and
under the criteria of the Regulatory maintenance manual or Instructions for Aerometals Aero–ICA–101
Flexibility Act. Continued Airworthiness (ICA). If the Supplemental Instructions for
We prepared an economic evaluation hours TIS on a pin is unknown, remove Continued Airworthiness, Revision NC,
of the estimated costs to comply with the pin from service. dated May 22, 2014, which are not
this proposed AD and placed it in the
(ii) For Model 369A, 369HE, 369HM, incorporated by reference, contain
AD docket.
and 369HS helicopters, if there is no pin additional information about the subject
List of Subjects in 14 CFR Part 39 life limit, establish a new life limit of of this AD. For service information
Air transportation, Aircraft, Aviation 5,760 hours TIS for each pin P/N identified in this AD, contact
safety, Incorporation by Reference, 369X1004–5 by making pen-and-ink Aerometals, 3920 Sandstone Dr., El
Safety. changes or by inserting a copy of this Dorado Hills, CA 95762, telephone (916)
AD into the Airworthiness Limitations 939–6888, fax (916) 939–6555,
The Proposed Amendment Section of the maintenance manual or www.aerometals.aero. You may review
Accordingly, under the authority the ICA. Remove from service any pin a copy of information at the FAA, Office
delegated to me by the Administrator, that has 5,760 or more hours TIS. of the Regional Counsel, Southwest
the FAA proposes to amend 14 CFR part (iii) For Model 369D, 369E, 369FF, Region, 10101 Hillwood Pkwy, Room
39 as follows: 500N, and 600N helicopters, if there is 6N–321, Fort Worth, TX 76177.
no pin life limit, establish a new life (h) Subject
PART 39—AIRWORTHINESS
limit of 7,600 hours TIS for each pin P/
DIRECTIVES Joint Aircraft Service Component
N 369X1004–5 by making pen-and-ink
(JASC) Code: 6210 Main Rotor Blades.
■ 1. The authority citation for part 39 changes or by inserting a copy of this
continues to read as follows: AD into the Airworthiness Limitations Issued in Fort Worth, Texas, on August 21,
Section of the maintenance manual or 2015.
Authority: 49 U.S.C. 106(g), 40113, 44701.
the ICA. Remove from service any pin Lance T. Gant,
§ 39.13 [Amended] that has 7,600 or more hours TIS. Acting Directorate Manager, Rotorcraft
■ 2. The FAA amends § 39.13 by adding (iv) For all model helicopters, add the Directorate, Aircraft Certification Service.
the following new airworthiness following statement to the [FR Doc. 2015–21680 Filed 9–1–15; 8:45 am]
directive (AD): Airworthiness Limitations Section of BILLING CODE 4910–13–P
MD Helicopters Inc.: Docket No. FAA–2015– the maintenance manual or the ICA by
3659; Directorate Identifier 2014–SW– making pen-and-ink changes or by
050–AD. inserting a copy of this AD: If DEPARTMENT OF TRANSPORTATION
(a) Applicability interchanged between different model
helicopters, the life limit of pin P/N Federal Aviation Administration
This AD applies to Model 369A, 369X1004–5 must be restricted to the
369D, 369E, 369FF, 369HE, 369HM, lowest life limit indicated for the 14 CFR Part 39
369HS, 500N, and 600N helicopters helicopter models and serial numbers [Docket No. FAA–2015–3658; Directorate
with an Aerometals main rotor blade affected. Identifier 2014–SW–039–AD]
attach pin (pin) part number (P/N)
369X1004–5 installed, certificated in (2) Do not install a pin P/N RIN 2120–AA64
any category. 369X1004–5 on any helicopter before
the requirements of this AD have been Airworthiness Directives; MD
(b) Unsafe Condition accomplished. Helicopters Inc. (MDHI) Helicopters
This AD defines the unsafe condition (f) Alternative Methods of Compliance AGENCY: Federal Aviation
as a pin remaining in service beyond its (AMOC) Administration (FAA), DOT.
fatigue life. This condition could result
in failure of a pin, loss of a main rotor ACTION: Notice of proposed rulemaking
(1) The Manager, Los Angeles Aircraft
blade, and subsequent loss of control of Certification Office, FAA, may approve (NPRM).
the helicopter. AMOCs for this AD. Send your proposal SUMMARY: We propose to adopt a new
(c) Comments Due Date to: Galib Abumeri, Aviation Safety airworthiness directive (AD) for certain
Engineer, Transport Airplane MDHI Model 369A (Army OH–6A),
We must receive comments by Directorate, FAA, 3960 Paramount
November 2, 2015. 369H, 369HE, 369HM, 369HS, 369D,
Blvd., Lakewood, California 90712; 369E, 369F, 369FF, and 500N
(d) Compliance telephone (562) 627–5324 or email at 9- helicopters. This proposed AD would
ANM-LAACO-AMOC- require inspecting the auxiliary fuel
You are responsible for performing REQUESTS@faa.gov.
each action required by this AD within pump (fuel pump) wire routing in the
(2) For operations conducted under a left-hand fuel cell and corrective action,
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
the specified compliance time unless it
has already been accomplished prior to 14 CFR part 119 operating certificate or if necessary. This proposed AD would
that time. under 14 CFR part 91, subpart K, we also require installing a warning decal
suggest that you notify your principal on the left-hand fuel cell access cover.
(e) Required Actions inspector, or lacking a principal This proposed AD is prompted by
(1) Within 100 hours time-in-service inspector, the manager of the local flight accidents resulting from incorrectly
(TIS) or during the next annual standards district office or certificate positioned fuel pump wiring within the
inspection, whichever occurs first: holding district office before operating fuel tank interfering with the operation
(i) Review the maintenance records any aircraft complying with this AD of the fuel quantity sensor float, which
and determine the hours TIS of each pin through an AMOC. caused an erroneous fuel quantity
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Document Created: 2018-02-26 10:10:49
Document Modified: 2018-02-26 10:10:49
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by November 2, 2015. | |
| 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 [email protected] | |
| FR Citation | 80 FR 53028 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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