CFR Part: "14 CFR Part 39"
RIN Number: "RIN 2120-AA64"
Citation: "79 FR 549"
Document Number: "Docket No.
"Rules and Regulations"
SUMMARY: We are adopting a new airworthiness directive (AD) for Sikorsky Model S-70, S-70A, S-70C, S-70C (M), and S-70C (M1) helicopters with
EFFECTIVE DATE: This AD is effective
The Director of the
ADDRESSES: For service information identified in this AD, contact
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
FOR FURTHER INFORMATION CONTACT:
The proposed actions in the SNPRM were intended to prevent failure of a GGT rotor part, engine failure, and subsequent loss of control of the helicopter.
We gave the public the opportunity to comment on the NPRM (77 FR 55166,
We have reviewed the relevant information and determined that an unsafe condition exists and is likely to exist or develop on other products of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed in the SNPRM (78 FR 44052,
Costs of Compliance
We estimate that this AD will affect 9 helicopters of U.S. registry. We estimate that operators may incur the following costs in order to comply with this AD: A minimal amount for work hours and labor costs because these parts are replaced as part of the periodic maintenance on the helicopter; a minimal amount of time to calculate the new retirement life;
Title 49 of the United States Code specifies the
We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: "General requirements." Under that section,
This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a "significant regulatory action" under Executive Order 12866;
(2) Is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034,
(3) Will not affect intrastate aviation in
(4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the Administrator, the
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.
This AD applies to Model S-70, S-70A, S-70C, S-70C (M), and S-70C (M1) helicopters with
(b) Unsafe Condition
This AD defines the unsafe condition as a critical engine part remaining in service beyond its fatigue life because the current life limit is based on hours time-in-service (TIS) instead of fatigue cycles. This condition could result in fatigue failure of an engine rotor part, engine failure, and subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective
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) Before further flight, insert into the airworthiness limitations section of the maintenance manual or instructions for continued airworthiness the low cycle fatigue (LCF) limit diagrams shown in Figures 2 through 7 (pages 9 through 14) of GE T700 Turboshaft Engine Service Bulletin T700 S/B 72-0041, Revision 1, dated
(2) Before further flight:
(i) Obtain the actual LCF1 and LCF2 count from the engine "history recorder" (HR);
(ii) Calculate the LCF1 and LCF2 fatigue retirement life for each GGT rotor part as follows:
(A) Determine the actual LCF ratio by dividing the total actual LCF2 cycle count obtained from the HR by the total actual LCF1 cycle count obtained from the HR. Add to the actual counts from the HR any actual additional fatigue cycle incurred during any period in which the HR was inoperative.
(B) Determine the LCF1 retirement life by dividing the maximum number of LCF2 events obtained from the applicable diagram for each engine by the sum of the actual LCF ratio obtained by following paragraph (e)(2)(ii)(A) of this AD plus the quotient of the maximum number of LCF2 events from the applicable diagram for each engine divided by the maximum number of LCF1 events from the applicable diagram for each engine.
(C) Determine the LCF2 retirement life by multiplying the actual LCF ratio obtained by following paragraph (e)(2)(ii)(A) of this AD times the LCF1 retirement life determined by following paragraph (e)(2)(ii)(B) of this AD.
(iii) Replace each GGT rotor part that has reached the new fatigue cycle life limit with an airworthy rotor part.
(3) For helicopters with the GE T700-GE-401C engine, if you cannot determine the number of low cycle fatigue events manually from the HR or by combining both manual and HR counts, then the life limit for the GGT rotor part is the hours TIS for the part as shown in Table 1 of GE T700 Turboshaft Engine Service Bulletin T700 S/B 72-0041, dated
(4) Before further flight, begin or continue to count the full and partial low fatigue cycle events and record on the component card or equivalent record that count at the end of each day for which the HR is inoperative.
(f) Special Flight Permit
Special flight permits will not be issued to allow flight in excess of life limits.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Boston Aircraft Certification Office,
(2) For operations conducted under 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.
Joint Aircraft Service Component (JASC) Code: 7250: Turbine Section.
(1) The Director of the
(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.
(ii) GE T700 Turboshaft Engine Service Bulletin T700 S/B 72-0041, dated
(iii) GE T700 Turboshaft Engine Service Bulletin T700 S/B 72-0041, Revision 1, dated
(3) For GE service information identified in this AD, contact
(4) You may view this service information at
(5) You may view this service information that is incorporated by reference at the
[FR Doc. 2013-31525 Filed 1-3-14;
BILLING CODE 4910-13-P
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