Document ID: FAA-2016-6968-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Sikorsky Aircraft Corporation Helicopters (Type Certificate Previously Held by Schweizer Aircraft Corporation)
Posted Date: 2017-01-05T05:00Z

[Federal Register Volume 82, Number 3 (Thursday, January 5, 2017)]
[Proposed Rules]
[Pages 1267-1269]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-31622]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6968; Directorate Identifier 2015-SW-020-AD]
RIN 2120-AA64

Airworthiness Directives; Sikorsky Aircraft Corporation 
Helicopters (Type Certificate Previously Held by Schweizer Aircraft 
Corporation)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede airworthiness directive (AD) 93-17-13 
for Schweizer Aircraft Corporation and Hughes Helicopters, Inc. (now 
Sikorsky Aircraft Corporation) (Sikorsky) Model TH55A, 269A, 269A-1, 
269B, and 269C helicopters. AD 93-17-13 requires installing tachometer 
markings and inspecting the driveshaft. This proposed AD would require 
recurring inspections of the driveshaft and would expand the 
applicability to include Model 269C-1 helicopters. This proposed AD is 
prompted by reports of accidents because of driveshaft failures. The 
actions of this proposed AD are intended to prevent the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by March 6, 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 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 
Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry 
Road, Trumbull, CT 06611; telephone 1-800-Winged-S or 203-416-4299; 
email wcs_cust_service_eng.gr-sik@lmco.com. 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: Blaine Williams, Aerospace Engineer, 
Boston Aircraft Certification Office, Engine & Propeller Directorate, 
1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 
238-7161; email blaine.williams@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 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

    On August 31, 1993, we issued AD 93-17-13, Amendment 39-8684 (58 FR 
51770, October 5, 1993), for Schweizer Aircraft Corporation and Hughes 
Helicopters, Inc., Model 269A, 269A-1, 269B, 269C, and TH55A 
helicopters. AD 93-17-13 requires within 30 days or 100 hours time-in-
service (TIS),

[[Page 1268]]

whichever occurs first, and thereafter every 300 hours TIS, visually 
inspecting for cracks, machining steps, manufacturing tool marks, 
surface defects, and lack of cleanup during the production grinding 
operation. AD 93-17-13 also requires installing engine and rotor 
tachomometer markings and replacing any unairworthy lower coupling 
driveshaft (driveshaft) before further flight. The actions in AD 93-17-
13 are intended to prevent failure of the driveshaft, loss of power to 
the rotor system, and subsequent loss of helicopter control.

Actions Since AD 93-17-13 Was Issued

    Since we issued AD 93-17-13, Sikorsky became the type certificate 
holder of the Model 269A, 269A-1, 269B, 269C, and TH55A. Sikorsky 
performed a safety analysis and determined that the initial and 
recurrent inspection intervals and inspection method were not adequate 
to detect all corrosion, pits, nicks, scratches, dents, and cracks. 
Since 1992, 10 accidents, 2 of them fatal, occurred because of 
driveshaft failures due to static overload or torsional fatigue. Five 
of the accidents occurred after AD 93-17-13 was issued.
    We propose reducing the initial and recurring inspection intervals, 
changing the type of damage to be detected by the visual inspection, 
and adding a magnetic particle inspection.
    We propose including specific part-numbered driveshafts to the 
applicability because Sikorsky is developing a new driveshaft that we 
do not expect to be subject to this AD.
    We propose expanding the applicability to include Model 269C-1 
helicopters. These helicopters were not manufactured when AD 93-17-13 
was issued but have applicable driveshafts installed.
    We propose to retain the requirement to install engine and 
tachometer markings. AD 93-17-13 requires these markings because of 
reports of driveshaft damage as a result of engine overspeeds during 
start-up.
    Finally, we would require a visual inspection for ``corrosion, a 
pit, a nick, a scratch, a dent, or a crack'' instead of ``cracks, 
machining steps, manufacturing tool marks, surface defects and lack of 
cleanup during the production grinding operation'' contained in AD 93-
17-13. Since AD 93-17-13 was issued, we have seen no evidence that the 
driveshaft failures were caused by production errors.
    The proposed actions are intended to prevent failure of the 
driveshaft, loss of power to the rotor system, and subsequent loss of 
helicopter control.

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 Under 1 CFR Part 51

    We reviewed Sikorsky 269C Helicopter Alert Service Bulletin B-307, 
Basic Issue, dated December 18, 2014, and Sikorsky 269C-1 Helicopter 
Alert Service Bulletin C1B-043, Basic Issue, dated December 18, 2014 
(ASBs). The ASBs call for a one-time visual and magnetic particle 
inspection of the driveshaft and driveshaft assembly for damage. The 
ASBs advise that the driveshaft be sent to Sikorsky and replaced if 
damaged. The inspection is to be accomplished within 25 hours TIS or 
within 180 days from the ASBs' issue date, whichever comes first. 
Sikorsky has since revised its maintenance manual to incorporate these 
inspections every 150 hours TIS.
    We also reviewed Schweizer Aircraft Service Bulletin B-257.1, dated 
May 21, 1993 (ASB B-257.1). ASB B-257.1 calls for a one-time inspection 
to look for drive-shaft defects; installing declutched limit markings 
on the engine/rotor tachometer to reinforce operating limits; and 
prohibiting engine declutched operations above 1,600 RPM.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Proposed AD Requirements

    This proposed AD would require within 25 hours TIS and thereafter 
at intervals not to exceed 150 hours TIS, visual inspections of the 
driveshaft. If there are no cracks, corrosion, or other damage, this 
proposed AD would require performing a magnetic particle inspection. If 
there is a crack or other damage, this proposed AD would require 
replacing the driveshaft before further flight. This proposed AD would 
also require adding tachometer markings if not previously performed.

Differences Between This Proposed AD and the Service Information

    The Sikorsky service information calls for the initial inspection 
to be completed within 180 days or 25 hours time-in-service (TIS). This 
proposed AD would require the initial inspection to be completed within 
25 hours TIS only. The service information requires contacting Sikorsky 
if a certain part-numbered driveshaft is installed, emailing 
information to Sikorsky, and returning damaged parts to Sikorsky; this 
proposed AD would not.

Interim Action

    We consider this proposed AD to be an interim action. The design 
approval holder is developing a replacement driveshaft that will 
address the unsafe condition identified in this proposed AD. Once the 
replacement driveshaft is developed, approved and available, we might 
consider additional rulemaking.

Costs of Compliance

    We estimate that this proposed AD would affect 619 helicopters of 
U.S. Registry and that labor costs average $85 per work hour. Based on 
these estimates, we expect the following costs:
     We estimate that the visual and magnetic particle 
inspections of the driveshaft would require 11 work hours for a cost of 
$935 per helicopter and $578,765 for the U.S. fleet per inspection 
cycle.
     Replacing the driveshaft, if needed, would cost about 
$4,574 for parts. No additional labor costs would be necessary.
     Installing engine and rotor tachometer markings would 
require 0.5 work-hour for a labor cost of about $43. The cost of parts 
would be minimal.

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

[[Page 1269]]

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, 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 removing Airworthiness Directive (AD) 
AD 93-17-13, Amendment 39-8684 (58 FR 51770, October 5, 1993) and 
adding the following new airworthiness directive (AD):

Sikorsky Aircraft Corporation (Type Certificate Previously Held By 
Schweizer Aircraft Corporation): Docket No. FAA-2016-6968; 
Directorate Identifier 2015-SW-020-AD.

(a) Applicability

    This AD applies to Model TH55A, 269A, 269A-1, 269B, 269C and 
269C-1 helicopters, with a lower coupling driveshaft (driveshaft) 
part number (P/N) 269-5412, 269A5504, 269A5504-003, 269A5504-005, 
269A5559, or 269A5559-003 installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of a driveshaft. 
This condition could result in loss of power to the rotor system and 
subsequent loss of helicopter control.

(c) Affected ADs

    This AD supersedes AD 93-17-13, Amendment 39-8684 (58 FR 51770, 
October 5, 1993).

(d) Comments Due Date

    We must receive comments by March 6, 2017.

(e) 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.

(f) Required Actions

    (1) Within 25 hours time-in-service (TIS), install engine and 
rotor tachometer markings in accordance with Part II of Schweizer 
Aircraft Service Bulletin B-257.1, dated May 21, 1993.
    (2) Within 25 hours TIS and thereafter at intervals not to 
exceed 150 hours TIS:
    (i) Visually inspect the driveshaft for corrosion, a pit, a 
nick, a scratch, a dent, and a crack in accordance with the 
Accomplishment Instructions, paragraph 3.B.(1) through 3.B.(6) of 
Sikorsky 269C Helicopter Alert Service Bulletin B-307, Basic Issue, 
dated December 18, 2014 (269C ASB), or Sikorsky 269C-1 Helicopter 
Alert Service Bulletin C1B-043, Basic Issue, dated December 18, 2014 
(269C-1 ASB), whichever is applicable for your model helicopter, 
except we do not require that you use a Sikorsky recommended vendor 
list. If there is any corrosion, a pit, a nick, a scratch, a dent, 
or a crack, replace the driveshaft before further flight.
    (ii) If there is no corrosion and no pits, nicks, scratches, 
dents, and cracks, magnetic particle inspect the driveshaft for a 
crack in accordance with paragraph 3.C.(1) of the 269C ASB or 269C-1 
ASB, whichever is applicable for your model helicopter. This 
magnetic particle inspection must be performed by a Level II or 
higher technician with the National Aerospace Standard 410 or 
equivalent certification who has performed a magnetic particle 
inspection within the last 12 months. If there is a crack, replace 
the driveshaft before further flight.

(g) Credit for Actions Previously Completed

    Compliance with paragraph (a)(1) of AD 93-17-13, Amendment 39-
8684 (58 FR 51770, October 5, 1993) before the effective date of 
this AD is considered acceptable for compliance with the actions 
specified in paragraph (f)(1) of this AD.

(h) Alternative Methods of Compliance (AMOC)

    (1) The Manager, Boston Aircraft Certification Office, FAA, may 
approve AMOCs for this AD. Send your proposal to: Blaine Williams, 
Aerospace Engineer, Boston Aircraft Certification Office, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, 
Massachusetts 01803; telephone (781) 238-7161; email 
blaine.williams@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.

(i) Additional Information

    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 
wcs_cust_service_eng.gr-sik@lmco.com. 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.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 6300, Main Rotor 
Drive System.

    Issued in Fort Worth, Texas, on December 21, 2016.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-31622 Filed 1-4-17; 8:45 am]
BILLING CODE 4910-13-P