82 FR 15120 - Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 57 (March 27, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 57 (March 27, 2017)
| Page Range | 15120-15123 | |
| FR Document | 2017-05967 |
[Federal Register Volume 82, Number 57 (Monday, March 27, 2017)] [Rules and Regulations] [Pages 15120-15123] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-05967] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9291; Directorate Identifier 2016-SW-004-AD; Amendment 39-18840; AD 2017-07-02] RIN 2120-AA64 Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model 269D and Model 269D Configuration A helicopters. This AD requires reducing the life limit of and inspecting certain drive shafts. This AD is prompted by four incidents involving failure of a drive shaft. The actions specified by this AD are intended to prevent the unsafe condition on these products. DATES: This AD becomes effective April 11, 2017. We must receive comments on this AD by May 26, 2017. 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 by searching for and locating Docket No. FAA-2016- 9291; 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 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 final rule, contact Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry Road, Trumbull, CT 06611; telephone 1-800-Winged-S or 203-416-4299; email: [email protected]. 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: Michael Schwetz, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, FAA, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238-7761; email [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, we invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the [[Page 15121]] economic, environmental, energy, or federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, 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 them 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 rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments. Discussion We are adopting a new AD for Sikorsky Model 269D and Model 269D Configuration A helicopters with KAflex drive shaft (engine side) part number (P/N) SKCP2738-7 and KAflex drive shaft (pulley side) P/N SKCP2738-5 installed. This AD is prompted by four incidents involving failure of the engine side drive shaft. Three incidents experienced loss of rotor drive resulting in forced landings. The fourth incident resulted in vibration during flight prompting an immediate landing. A fractured engine side drive shaft was evident in each incident. Investigations revealed compression of the rubber engine mounts may lead to loss of alignment between the lower pulley shaft and the engine output shaft, resulting in fracture of the engine side drive shaft. Additionally, it has been discovered that increased cyclic torsional loading was inaccurately applied in previous fatigue analysis, making it necessary to reduce the life limit. Accordingly, this AD requires reducing the life limit of the engine side drive shaft and pulley side drive shaft to 6,000 hours time-in- service (TIS) for Model 269D helicopters and 1,200 hours TIS for Model 269D Configuration A helicopters. If the drive shaft is interchanged or has ever been interchanged between the two model configurations, this AD requires using the lower life limit of 1,200 hours TIS. This AD also requires performing several inspections of the drive shaft within 25 hours TIS and, depending on the results of these inspections, replacing both the engine side and pulley side drive shafts. The actions specified by this AD are intended to prevent failure of the drive shaft, loss of rotor drive, and subsequent loss of control of the helicopter. Additional inspections at longer intervals may also be necessary. We plan to publish a notice of proposed rulemaking to give the public an opportunity to comment on those long-term requirements. Record of Ex Parte Communication In preparation of AD actions such as notices of proposed rulemaking and immediately adopted final rules, it is the practice of the FAA to obtain technical information and information on the operational and economic impact from design approval holders and aircraft operators. We discussed certain aspects of this AD by email and telephone with Sikorsky. A copy of each email contact and a discussion of each telephone contact can be found in the rulemaking docket. For information on locating the docket, see ``Examining the AD Docket.'' FAA's Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type designs. Related Service Information We reviewed Appendix B to Sikorsky S-330 Model 269D Helicopter Basic Handbook of Maintenance Instructions No. CSP-D-2, dated February 1, 1993, and revised October 15, 2014; and Appendix B to Sikorsky S-333 Model 269D Config. ``A'' Helicopter Basic Handbook of Maintenance Instructions No. CSP-D-9, dated July 20, 2001, and revised October 15, 2014. This service information specifies repetitive inspection procedures, overhaul and retirement schedules, and weight and balance procedures. The Airworthiness Limitations section, which is included in this service information, contains the life limits for drive shaft assembly P/Ns SKCP2738-5 and SKCP2738-7. We also reviewed Sikorsky 269D Helicopter Alert Service Bulletin DB-052, Basic Issue, dated January 16, 2014, which distributes the service life reduction information and implements a new 1,200-hour overhaul inspection for drive shaft assembly P/Ns SKCP2738-3, SKCP2738- 5, and SKCP2738-7. AD Requirements This AD requires, before further flight: Removing from service any engine side drive shaft P/N SKCP2738-7 and pulley side drive shaft P/N SKCP2738-5 that has reached or exceeded its new life limit as follows: [cir] 6,000 hours TIS for Model 269D helicopters; [cir] 1,200 hours TIS for Model 269D Configuration A helicopters; and [cir] 1,200 hours TIS if the parts have ever been interchanged between the two model configurations. This AD also requires, within 25 hours TIS: Inspecting the KAflex drive shaft alignment. Inspecting the engine side and pulley side drive shafts for a crack, any corrosion or pitting, a nick, a dent, and a scratch. Inspecting each bolted joint (joint) for movement. Inspecting each joint for fretting corrosion and each frame and mount bolt torque stripe for movement. Inspecting each joint for fretting, for a crack around both the bolt head and washer side, and around the nut and washer side, and each inside and outside corner radii and radii edges on both sides of each frame for a crack. If the drive shaft fails any of the above inspections, this AD requires replacing both the engine side and pulley side drive shafts before further flight. Lastly, this AD requires within 25 hours TIS and thereafter at intervals not to exceed 25 hours TIS: Inspecting the lower pulley to engine alignment, and if there is any interference with the rotation of the belt drive alignment tool, adjusting the engine elevation alignment before further flight. This AD also specifies installing KAflex engine side coupling assembly P/N SKCP2738-9 and KAflex pulley side coupling assembly P/N SKCP2738-101 as an optional terminating action for the requirements of this AD. Differences Between This AD and the Service Information The Sikorsky service information specifies a drive shaft assembly service life of 3,000 hours TIS with a 1,200 hour overhaul inspection for Model 269D Configuration A helicopters, while this AD specifies a service life of 1,200 hours TIS. This AD specifies several inspections with a compliance time of 25 hours TIS that are currently recurring inspections at 100-hour or 400- hour intervals in Sikorsky's service information. The Sikorsky service information specifies different inspection procedures if there is spline engagement interference or resistance while inspecting the drive shaft alignment. This AD specifies replacing both the engine side and pulley side drive shafts if there is any spline engagement interference or resistance. The Sikorsky service information specifies inspecting the working [[Page 15122]] fastener condition without any specific succeeding action regarding the inspection. This AD specifies replacing both the engine side and pulley side drive shafts if there is any joint movement. The Sikorsky service information specifies returning the drive shaft assembly to Sikorsky if there is fretting dust or red metallic residue at a joint. This AD specifies replacing both the engine side and pulley side drive shafts if there is any fretting corrosion. Interim Action We consider this AD interim action. If final action is later identified, we might consider further rulemaking then. Costs of Compliance We estimate that this AD affects 18 helicopters of U.S. Registry. We estimate that operators may incur the following costs to comply with this AD. Labor costs are estimated at $85 per work-hour. Removing the engine side and pulley side drive shafts that have reached the new life limit will take about 4 work-hours for a cost of $340 per helicopter. Inspecting the drive shaft alignment will take about 1 work-hour for a cost of $85 per helicopter and $1,530 for the U.S. fleet. Inspecting the drive shafts for damage will take about 1 work-hour for an estimated cost of $85 per helicopter and $1,530 for the U.S. fleet. Inspecting the joints will take about 1 work-hour for an estimated cost of $85 per helicopter and $1,530 for the U.S. fleet. Replacing the engine side and pulley side drive shafts, if required, will take about 8 work-hours and parts will cost about $20,000, for an estimated cost of $20,680 per helicopter. Inspecting the lower pulley to engine alignment will take about 0.5 work-hour for an estimated cost of $43 per helicopter and $774 for the U.S. fleet per inspection cycle. Adjusting the engine elevation alignment will take about 0.5 work-hour for an estimated cost of $43 per helicopter. FAA's Justification and Determination of the Effective Date Providing an opportunity for public comments prior to adopting these AD requirements would delay implementing the safety actions needed to correct this known unsafe condition. Therefore, we find that the risk to the flying public justifies waiving notice and comment prior to the adoption of this rule because some of the required corrective actions must be completed before further flight. Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and opportunity for public comment before issuing this AD are impracticable and contrary to the public interest and that good cause exists for making this amendment effective in less than 30 days. 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 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, 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, 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 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 FAA amends 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): 2017-07-02 Sikorsky Aircraft Corporation (Sikorsky): Amendment 39- 18840; Docket No. FAA-2016-9291; Directorate Identifier 2016-SW-004- AD. (a) Applicability This AD applies to Sikorsky Model 269D and Model 269D Configuration A helicopters with a KAflex engine side drive shaft part number (P/N) SKCP2738-7 and KAflex pulley side drive shaft P/N SKCP2738-5 installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as failure of a drive shaft. This condition could result in loss of rotor drive and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective April 11, 2017. (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) Before further flight: (i) For Model 269D helicopters, remove from service any KAflex engine side drive shaft P/N SKCP2738-7 and any KAflex pulley side drive shaft P/N SKCP2738-5 that has 6,000 or more hours time-in- service (TIS). Thereafter, remove from service any KAflex engine side drive shaft P/N SKCP2738-7 and any KAflex pulley side drive shaft P/N SKCP2738-5 before accumulating 6,000 hours TIS. (ii) For Model 269D Configuration A helicopters, remove from service any KAflex engine side drive shaft P/N SKCP2738-7 and any KAflex pulley side drive shaft P/N SKCP2738-5 that has 1,200 or more hours TIS. Thereafter, remove from service any KAflex engine side drive shaft P/N SKCP2738-7 and any KAflex pulley side drive shaft P/ N SKCP2738-5 before accumulating 1,200 hours TIS. (iii) If interchanged between Model 269D and Model 269D Configuration A helicopters, remove from service any KAflex engine side drive shaft P/N SKCP2738-7 and any KAflex pulley side drive shaft P/N SKCP2738-5 that has 1,200 or more hours TIS. Thereafter, if interchanged between Model 269D and Model 269D Configuration A helicopters, remove from service any KAflex engine side drive shaft P/N SKCP2738-7 and any KAflex pulley side drive shaft P/N SKCP2738-5 before accumulating 1,200 hours TIS. [[Page 15123]] (2) Within 25 hours TIS: (i) Remove the drive shaft to adapter bolt and inspect the drive shaft alignment. Engage and disengage the splines a minimum of 3 times by sliding the engine power output shaft in and out of the engine. Inspect the alignment at each 90[deg] interval by rotating the lower pulley with the power shaft disengaged. Determine whether the adapter slides on and off the drive shaft splines without spline engagement interference or resistance along the entire length of movement. If there is any spline engagement interference or resistance, before further flight, replace both the engine side and pulley side drive shafts. (ii) Inspect each drive shaft for a crack, any corrosion or pitting, a nick, a dent, and a scratch. If there is a crack, any corrosion or pitting, a nick, a dent, or a scratch that exceeds allowable limits, before further flight, replace both the engine side and pulley side drive shafts. (iii) Remove the engine side drive shaft and pulley side drive shaft and perform the following: (A) Inspect each flex frame (frame) bolted joint (joint) for movement by hand. If there is any movement, before further flight, replace both the engine side and pulley side drive shafts. (B) Visually inspect each joint for fretting corrosion (which might be indicated by metallic particles) and each frame and mount bolt torque stripe for movement. If there is any fretting corrosion or torque stripe movement, before further flight, replace both the engine side and pulley side drive shafts. (C) Using a 10x or higher power magnifying glass, visually inspect each joint for fretting and for a crack around the bolt head and washer side, and around the nut and washer side. Also inspect both sides of each frame for a crack on the inside and outside corner radii and radii edge (four). If there is any fretting, a crack at any point over the full circumference (360[deg]) of the bolt head and washer side or the nut and washer side, or a crack in any of the corner radii edges, before further flight, replace both the engine side and pulley side drive shafts. (iv) Using a belt drive alignment tool 269T3303-003, inspect the lower pulley to engine alignment by engaging the tool on the drive shaft and inserting in the lower pulley bore. Rotate the tool 360[deg] around the drive shaft and inspect for interference. If there is any interference with the rotation of the tool, before further flight, adjust the engine elevation alignment to eliminate the interference. (3) Thereafter, at intervals not to exceed 25 hours TIS, repeat the actions specified in paragraph (e)(2)(iv) of this AD. (4) As an optional terminating action to the repetitive inspections in this AD, you may install KAflex engine side drive shaft P/N SKCP2738-9 and KAflex pulley side drive shaft P/N SKCP2738-101. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Boston Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Michael Schwetz, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, FAA, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238-7761; email [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 Sikorsky 269D Helicopter Alert Service Bulletin DB-052, Basic Issue, dated January 16, 2014; Appendix B of Sikorsky S-330 Model 269D Helicopter Basic Handbook of Maintenance Instructions, No. CSP- D-2, dated February 1, 1993, and revised October 15, 2014; and Appendix B of Sikorsky S-330 Model 269D Config. ``A'' Helicopter Basic Handbook of Maintenance Instructions, No. CSP-D-9, dated July 20, 2001, and revised October 15, 2014; which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry Road, Trumbull, CT 06611; telephone 1-800-Winged-S or 203- 416-4299; email: [email protected]. You may review this service 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: 6310, Engine/ Transmission Coupling. Issued in Fort Worth, Texas, on March 20, 2017. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2017-05967 Filed 3-24-17; 8:45 am] BILLING CODE 4910-13-P
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(i) No Reporting Requirement (IBR) of the service information listed in this We must receive comments on this
Although Airbus Service Bulletin A300– paragraph under 5 U.S.C. 552(a) and 1 CFR AD by May 26, 2017.
53–6184, dated November 12, 2015, specifies part 51.
ADDRESSES: You may send comments by
to submit certain information to the (2) You must use this service information
as applicable to do the actions required by any of the following methods:
manufacturer, and specifies that action as RC, • Federal eRulemaking Docket: Go to
this AD does not include that requirement. this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A300–53–6184, http://www.regulations.gov. Follow the
(j) Other FAA AD Provisions dated November 12, 2015. online instructions for sending your
The following provisions also apply to this (ii) Reserved. comments electronically.
AD: (3) For service information identified in • Fax: 202–493–2251.
(1) Alternative Methods of Compliance this AD, contact Airbus SAS, Airworthiness • Mail: Send comments to the U.S.
(AMOCs): The Manager, International Office—EAW, 1 Rond Point Maurice Department of Transportation, Docket
Branch, ANM–116, Transport Airplane Bellonte, 31707 Blagnac Cedex, France; Operations, M–30, West Building
Directorate, FAA, has the authority to telephone +33 5 61 93 36 96; fax +33 5 61
Ground Floor, Room W12–140, 1200
approve AMOCs for this AD, if requested 93 44 51; email account.airworth-eas@
using the procedures found in 14 CFR 39.19. airbus.com; Internet http://www.airbus.com. New Jersey Avenue SE., Washington,
In accordance with 14 CFR 39.19, send your (4) You may view this service information DC 20590–0001.
request to your principal inspector or local at the FAA, Transport Airplane Directorate, • Hand Delivery: Deliver to the
Flight Standards District Office, as 1601 Lind Avenue SW., Renton, WA. For ‘‘Mail’’ address between 9 a.m. and 5
appropriate. If sending information directly information on the availability of this p.m., Monday through Friday, except
to the International Branch, send it to ATTN: material at the FAA, call 425–227–1221. Federal holidays.
Dan Rodina, Aerospace Engineer, (5) You may view this service information
International Branch, ANM–116, Transport that is incorporated by reference at the Examining the AD Docket
Airplane Directorate, FAA, 1601 Lind National Archives and Records You may examine the AD docket on
Avenue SW., Renton, WA 98057–3356; Administration (NARA). For information on the Internet at http://
telephone 425–227–2125; fax 425–227–1149; the availability of this material at NARA, call
email dan.rodina@faa.gov. Information may 202–741–6030, or go to: http://
www.regulations.gov by searching for
be emailed to: 9-ANM-116-AMOC- www.archives.gov/federal-register/cfr/ibr- and locating Docket No. FAA–2016–
REQUESTS@faa.gov. Before using any locations.html. 9291; or in person at the Docket
approved AMOC, notify your appropriate Operations Office between 9 a.m. and 5
Issued in Renton, Washington, on March 8,
principal inspector, or lacking a principal
2017.
p.m., Monday through Friday, except
inspector, the manager of the local flight Federal holidays. The AD docket
standards district office/certificate holding Michael Kaszycki,
contains this AD, the economic
district office. Acting Manager, Transport Airplane evaluation, any comments received, and
(2) Contacting the Manufacturer: For any Directorate, Aircraft Certification Service.
other information. The street address for
requirement in this AD to obtain corrective [FR Doc. 2017–05231 Filed 3–24–17; 8:45 am]
actions from a manufacturer, the action must
the Docket Operations Office (telephone
BILLING CODE 4910–13–P 800–647–5527) is in the ADDRESSES
be accomplished using a method approved
by the Manager, International Branch, ANM– section. Comments will be available in
116, Transport Airplane Directorate, FAA; or the AD docket shortly after receipt.
DEPARTMENT OF TRANSPORTATION For service information identified in
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Federal Aviation Administration this final rule, contact Sikorsky Aircraft
Organization Approval (DOA). If approved by Corporation, Customer Service
the DOA, the approval must include the Engineering, 124 Quarry Road,
DOA-authorized signature. 14 CFR Part 39
Trumbull, CT 06611; telephone 1–800–
(3) Required for Compliance (RC): Except
[Docket No. FAA–2016–9291; Directorate Winged–S or 203–416–4299; email:
as required by paragraphs (h) and (i) of this
AD: If any service information contains Identifier 2016–SW–004–AD; Amendment wcs_cust_service_eng.gr-sik@lmco.com.
procedures or tests that are identified as RC, 39–18840; AD 2017–07–02] You may review the referenced service
those procedures and tests must be done to information at the FAA, Office of the
RIN 2120–AA64 Regional Counsel, Southwest Region,
comply with this AD; any procedures or tests
that are not identified as RC are 10101 Hillwood Pkwy., Room 6N–321,
recommended. Those procedures and tests
Airworthiness Directives; Sikorsky
Fort Worth, TX 76177.
that are not identified as RC may be deviated Aircraft Corporation Helicopters
FOR FURTHER INFORMATION CONTACT:
from using accepted methods in accordance AGENCY: Federal Aviation
with the operator’s maintenance or
Michael Schwetz, Aviation Safety
inspection program without obtaining
Administration (FAA), DOT. Engineer, Boston Aircraft Certification
approval of an AMOC, provided the ACTION: Final rule; request for Office, Engine & Propeller Directorate,
procedures and tests identified as RC can be comments. FAA, 1200 District Avenue, Burlington,
done and the airplane can be put back in an Massachusetts 01803; telephone (781)
airworthy condition. Any substitutions or SUMMARY: We are adopting a new 238–7761; email michael.schwetz@
changes to procedures or tests identified as airworthiness directive (AD) for faa.gov.
RC require approval of an AMOC. Sikorsky Aircraft Corporation (Sikorsky)
SUPPLEMENTARY INFORMATION:
(k) Related Information Model 269D and Model 269D
Configuration A helicopters. This AD Comments Invited
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD requires reducing the life limit of and This AD is a final rule that involves
2016–0057, dated March 18, 2016, for related inspecting certain drive shafts. This AD requirements affecting flight safety, and
pmangrum on DSK3GDR082PROD with RULES
information. This MCAI may be found in the is prompted by four incidents involving we did not provide you with notice and
AD docket on the Internet at http:// failure of a drive shaft. The actions an opportunity to provide your
www.regulations.gov by searching for and specified by this AD are intended to comments prior to it becoming effective.
locating Docket No. FAA–2016–9051. prevent the unsafe condition on these However, we invite you to participate in
(l) Material Incorporated by Reference products. this rulemaking by submitting written
(1) The Director of the Federal Register DATES: This AD becomes effective April comments, data, or views. We also
approved the incorporation by reference 11, 2017. invite comments relating to the
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fastener condition without any specific opportunity for public comment before the FAA amends 14 CFR part 39 as
succeeding action regarding the issuing this AD are impracticable and follows:
inspection. This AD specifies replacing contrary to the public interest and that
both the engine side and pulley side good cause exists for making this PART 39—AIRWORTHINESS
drive shafts if there is any joint amendment effective in less than 30 DIRECTIVES
movement. days.
The Sikorsky service information ■ 1. The authority citation for part 39
specifies returning the drive shaft Authority for This Rulemaking continues to read as follows:
assembly to Sikorsky if there is fretting Title 49 of the United States Code Authority: 49 U.S.C. 106(g), 40113, 44701.
dust or red metallic residue at a joint. specifies the FAA’s authority to issue
§ 39.13 [Amended]
This AD specifies replacing both the rules on aviation safety. Subtitle I,
engine side and pulley side drive shafts section 106, describes the authority of ■ 2. The FAA amends § 39.13 by adding
if there is any fretting corrosion. the FAA Administrator. ‘‘Subtitle VII: the following new airworthiness
Aviation Programs,’’ describes in more directive (AD):
Interim Action
detail the scope of the Agency’s 2017–07–02 Sikorsky Aircraft Corporation
We consider this AD interim action. If authority. (Sikorsky): Amendment 39–18840;
final action is later identified, we might We are issuing this rulemaking under Docket No. FAA–2016–9291; Directorate
consider further rulemaking then. the authority described in ‘‘Subtitle VII, Identifier 2016–SW–004–AD.
Costs of Compliance Part A, Subpart III, Section 44701: (a) Applicability
General requirements.’’ Under that This AD applies to Sikorsky Model 269D
We estimate that this AD affects 18 section, Congress charges the FAA with and Model 269D Configuration A helicopters
helicopters of U.S. Registry. We estimate promoting safe flight of civil aircraft in with a KAflex engine side drive shaft part
that operators may incur the following air commerce by prescribing regulations number (P/N) SKCP2738–7 and KAflex
costs to comply with this AD. Labor for practices, methods, and procedures pulley side drive shaft P/N SKCP2738–5
costs are estimated at $85 per work- the Administrator finds necessary for installed, certificated in any category.
hour. Removing the engine side and safety in air commerce. This regulation (b) Unsafe Condition
pulley side drive shafts that have is within the scope of that authority
reached the new life limit will take This AD defines the unsafe condition as
because it addresses an unsafe condition failure of a drive shaft. This condition could
about 4 work-hours for a cost of $340 that is likely to exist or develop on result in loss of rotor drive and subsequent
per helicopter. Inspecting the drive shaft products identified in this rulemaking loss of control of the helicopter.
alignment will take about 1 work-hour action.
for a cost of $85 per helicopter and (c) Effective Date
$1,530 for the U.S. fleet. Inspecting the Regulatory Findings This AD becomes effective April 11, 2017.
drive shafts for damage will take about We determined that this AD will not (d) Compliance
1 work-hour for an estimated cost of $85 have federalism implications under You are responsible for performing each
per helicopter and $1,530 for the U.S. Executive Order 13132. This AD will action required by this AD within the
fleet. Inspecting the joints will take not have a substantial direct effect on specified compliance time unless it has
about 1 work-hour for an estimated cost the States, on the relationship between already been accomplished prior to that time.
of $85 per helicopter and $1,530 for the the national Government and the States, (e) Required Actions
U.S. fleet. Replacing the engine side and or on the distribution of power and (1) Before further flight:
pulley side drive shafts, if required, will responsibilities among the various (i) For Model 269D helicopters, remove
take about 8 work-hours and parts will levels of government. from service any KAflex engine side drive
cost about $20,000, for an estimated cost For the reasons discussed, I certify shaft P/N SKCP2738–7 and any KAflex
of $20,680 per helicopter. Inspecting the that this AD: pulley side drive shaft P/N SKCP2738–5 that
lower pulley to engine alignment will 1. Is not a ‘‘significant regulatory has 6,000 or more hours time-in-service
take about 0.5 work-hour for an action’’ under Executive Order 12866; (TIS). Thereafter, remove from service any
estimated cost of $43 per helicopter and 2. Is not a ‘‘significant rule’’ under KAflex engine side drive shaft P/N
$774 for the U.S. fleet per inspection SKCP2738–7 and any KAflex pulley side
DOT Regulatory Policies and Procedures drive shaft P/N SKCP2738–5 before
cycle. Adjusting the engine elevation (44 FR 11034, February 26, 1979); accumulating 6,000 hours TIS.
alignment will take about 0.5 work-hour 3. Will not affect intrastate aviation in (ii) For Model 269D Configuration A
for an estimated cost of $43 per Alaska to the extent that it justifies helicopters, remove from service any KAflex
helicopter. making a regulatory distinction; and engine side drive shaft P/N SKCP2738–7 and
4. Will not have a significant any KAflex pulley side drive shaft P/N
FAA’s Justification and Determination SKCP2738–5 that has 1,200 or more hours
economic impact, positive or negative,
of the Effective Date TIS. Thereafter, remove from service any
on a substantial number of small entities
Providing an opportunity for public KAflex engine side drive shaft P/N
under the criteria of the Regulatory SKCP2738–7 and any KAflex pulley side
comments prior to adopting these AD Flexibility Act. drive shaft P/N SKCP2738–5 before
requirements would delay We prepared an economic evaluation accumulating 1,200 hours TIS.
implementing the safety actions needed of the estimated costs to comply with (iii) If interchanged between Model 269D
to correct this known unsafe condition. this AD and placed it in the AD docket. and Model 269D Configuration A helicopters,
Therefore, we find that the risk to the remove from service any KAflex engine side
flying public justifies waiving notice List of Subjects in 14 CFR Part 39 drive shaft P/N SKCP2738–7 and any KAflex
pmangrum on DSK3GDR082PROD with RULES
and comment prior to the adoption of Air transportation, Aircraft, Aviation pulley side drive shaft P/N SKCP2738–5 that
this rule because some of the required has 1,200 or more hours TIS. Thereafter, if
safety, Incorporation by Reference,
interchanged between Model 269D and
corrective actions must be completed Safety. Model 269D Configuration A helicopters,
before further flight. remove from service any KAflex engine side
Since an unsafe condition exists that Adoption of the Amendment
drive shaft P/N SKCP2738–7 and any KAflex
requires the immediate adoption of this Accordingly, under the authority pulley side drive shaft P/N SKCP2738–5
AD, we determined that notice and delegated to me by the Administrator, before accumulating 1,200 hours TIS.
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![Federal Register / Vol. 82, No. 57 / Monday, March 27, 2017 / Rules and Regulations 15123
(2) Within 25 hours TIS: Boston Aircraft Certification Office, Engine & report indicating that the fire block in
(i) Remove the drive shaft to adapter bolt Propeller Directorate, FAA, 1200 District the closets and video control stations,
and inspect the drive shaft alignment. Engage Avenue, Burlington, Massachusetts 01803; and fire blocking tape in the floor panel
and disengage the splines a minimum of 3 telephone (781) 238–7761; email
opening in the forward and aft main
times by sliding the engine power output michael.schwetz@faa.gov.
shaft in and out of the engine. Inspect the (2) For operations conducted under a 14 passenger cabin, might be missing on
alignment at each 90° interval by rotating the CFR part 119 operating certificate or under some airplanes. This AD requires
lower pulley with the power shaft 14 CFR part 91, subpart K, we suggest that installing a fire block in the closets and
disengaged. Determine whether the adapter you notify your principal inspector, or video control stations, as applicable,
slides on and off the drive shaft splines lacking a principal inspector, the manager of and installing fire blocking tape in the
without spline engagement interference or the local flight standards district office or floor panel openings in the forward and
resistance along the entire length of certificate holding district office before aft main passenger cabin. We are issuing
movement. If there is any spline engagement operating any aircraft complying with this
this AD to address the unsafe condition
interference or resistance, before further AD through an AMOC.
flight, replace both the engine side and on these products.
(g) Additional Information
pulley side drive shafts. DATES: This AD is effective May 1, 2017.
(ii) Inspect each drive shaft for a crack, any Sikorsky 269D Helicopter Alert Service
corrosion or pitting, a nick, a dent, and a Bulletin DB–052, Basic Issue, dated January The Director of the Federal Register
scratch. If there is a crack, any corrosion or 16, 2014; Appendix B of Sikorsky S–330 approved the incorporation by reference
pitting, a nick, a dent, or a scratch that Model 269D Helicopter Basic Handbook of of certain publications listed in this AD
exceeds allowable limits, before further Maintenance Instructions, No. CSP–D–2, as of May 1, 2017.
flight, replace both the engine side and dated February 1, 1993, and revised October
pulley side drive shafts. 15, 2014; and Appendix B of Sikorsky S–330 ADDRESSES: For service information
(iii) Remove the engine side drive shaft and Model 269D Config. ‘‘A’’ Helicopter Basic identified in this final rule, contact
pulley side drive shaft and perform the Handbook of Maintenance Instructions, No. Boeing Commercial Airplanes,
following: CSP–D–9, dated July 20, 2001, and revised Attention: Contractual & Data Services
(A) Inspect each flex frame (frame) bolted October 15, 2014; which are not incorporated (C&DS), 2600 Westminster Blvd., MC
joint (joint) for movement by hand. If there by reference, contain additional information 110–SK57, Seal Beach, CA 90740;
is any movement, before further flight, about the subject of this AD. For service telephone 562–797–1717; Internet
replace both the engine side and pulley side information identified in this AD, contact
Sikorsky Aircraft Corporation, Customer
https://www.myboeingfleet.com. You
drive shafts. may view this referenced service
(B) Visually inspect each joint for fretting Service Engineering, 124 Quarry Road,
corrosion (which might be indicated by Trumbull, CT 06611; telephone 1–800– information at the FAA, Transport
metallic particles) and each frame and mount Winged–S or 203–416–4299; email: wcs_ Airplane Directorate, 1601 Lind Avenue
bolt torque stripe for movement. If there is cust_service_eng.gr-sik@lmco.com. You may SW., Renton, WA. For information on
any fretting corrosion or torque stripe review this service information at the FAA, the availability of this material at the
movement, before further flight, replace both Office of the Regional Counsel, Southwest FAA, call 425–227–1221. It is also
the engine side and pulley side drive shafts. Region, 10101 Hillwood Pkwy, Room 6N– available on the Internet at http://
(C) Using a 10x or higher power 321, Fort Worth, TX 76177. www.regulations.gov by searching for
magnifying glass, visually inspect each joint (h) Subject and locating Docket No. FAA–2016–
for fretting and for a crack around the bolt 8844.
head and washer side, and around the nut Joint Aircraft Service Component (JASC)
and washer side. Also inspect both sides of Code: 6310, Engine/Transmission Coupling. Examining the AD Docket
each frame for a crack on the inside and Issued in Fort Worth, Texas, on March 20,
outside corner radii and radii edge (four). If 2017. You may examine the AD docket on
there is any fretting, a crack at any point over Scott A. Horn, the Internet at http://
the full circumference (360°) of the bolt head www.regulations.gov by searching for
Acting Manager, Rotorcraft Directorate,
and washer side or the nut and washer side, and locating Docket No. FAA–2016–
Aircraft Certification Service.
or a crack in any of the corner radii edges, 8844; or in person at the Docket
before further flight, replace both the engine [FR Doc. 2017–05967 Filed 3–24–17; 8:45 am]
Management Facility between 9 a.m.
side and pulley side drive shafts. BILLING CODE 4910–13–P
(iv) Using a belt drive alignment tool and 5 p.m., Monday through Friday,
269T3303–003, inspect the lower pulley to except Federal holidays. The AD docket
engine alignment by engaging the tool on the DEPARTMENT OF TRANSPORTATION contains this AD, the regulatory
drive shaft and inserting in the lower pulley evaluation, any comments received, and
bore. Rotate the tool 360° around the drive Federal Aviation Administration other information. The address for the
shaft and inspect for interference. If there is Docket Office (phone: 800–647–5527) is
any interference with the rotation of the tool, 14 CFR Part 39 Docket Management Facility, U.S.
before further flight, adjust the engine Department of Transportation, Docket
elevation alignment to eliminate the [Docket No. FAA–2016–8844; Directorate
Operations, M–30, West Building
interference. Identifier 2016–NM–026–AD; Amendment
(3) Thereafter, at intervals not to exceed 25 39–18833; AD 2017–06–09] Ground Floor, Room W12–140, 1200
hours TIS, repeat the actions specified in New Jersey Avenue SE., Washington,
paragraph (e)(2)(iv) of this AD. RIN 2120–AA64 DC 20590.
(4) As an optional terminating action to the FOR FURTHER INFORMATION CONTACT:
repetitive inspections in this AD, you may Airworthiness Directives; The Boeing
install KAflex engine side drive shaft P/N Company Airplanes Susan L. Monroe, Aerospace Engineer,
SKCP2738–9 and KAflex pulley side drive Cabin Safety and Environmental
AGENCY: Federal Aviation
pmangrum on DSK3GDR082PROD with RULES
shaft P/N SKCP2738–101. Systems Branch, ANM–150S, FAA,
Administration (FAA), DOT. Seattle Aircraft Certification Office
(f) Alternative Methods of Compliance ACTION: Final rule. (ACO), 1601 Lind Avenue SW., Renton,
(AMOCs)
WA 98057–3356; phone: 425–917–6457;
(1) The Manager, Boston Aircraft SUMMARY: We are adopting a new
fax: 425–917–6590; email:
Certification Office, FAA, may approve airworthiness directive (AD) for certain
susan.l.monroe@faa.gov.
AMOCs for this AD. Send your proposal to: The Boeing Company Model 787–8
Michael Schwetz, Aviation Safety Engineer, airplanes. This AD was prompted by a SUPPLEMENTARY INFORMATION:
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Document Created: 2017-03-25 00:20:55
Document Modified: 2017-03-25 00:20:55
| 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 | Rules and Regulations | |
| Action | Final rule; request for comments. | |
| Dates | This AD becomes effective April 11, 2017. | |
| Contact | Michael Schwetz, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, FAA, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238-7761; email [email protected] | |
| FR Citation | 82 FR 15120 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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