[Federal Register Volume 65, Number 128 (Monday, July 3, 2000)]
[Rules and Regulations]
[Pages 40988-40990]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-16356]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-18-AD; Amendment 39-11805; AD 2000-13-06]
RIN 2120-AA64


Airworthiness Directives; Sikorsky Model S-61 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) for Sikorsky Model S-61 helicopters. That AD requires inspecting 
certain pylon upper and lower hinge web fittings (web fittings) for 
corrosion or a crack and either repairing certain web fittings or 
replacing any unairworthy web fittings with airworthy web fittings. 
That AD also requires creating a log card or equivalent record and 
implementing a recurring inspection of the web fittings. This amendment 
retains the requirements of that AD but corrects an error in paragraph 
(a)(3) by removing the words ``and 3.E.'' This amendment is prompted by 
an operator notifying the FAA of that error which requires an 
unnecessary major inspection within 25 hours time-in-service (TIS). The 
actions specified in this AD are intended to remove an undue burden on 
the public by superseding the AD and removing the requirement for the 
major inspection within 25 hours TIS.

DATES: Effective July 18, 2000.
    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of March 30, 2000 (65 FR 13877, March 15, 2000).
    Comments for inclusion in the Rules Docket must be received on or 
before September 1, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2000-SW-18-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: <a href="/cdn-cgi/l/email-protection#3d04105c4e4a105c595e5250505853494e7d5b5c5c135a524b"><span class="__cf_email__" data-cfemail="e1d8cc809296cc8085828e8c8c848f9592a1878080cf868e97">[email protected]</span></a>.
    The service information referenced in this AD may be obtained from 
Sikorsky Aircraft Corporation, Attn: Manager, Commercial Tech Support, 
6900 Main Street, P. O. Box 9729, Stratford, Connecticut 06497-9129, 
phone (203) 386-7860, fax (203) 386-4703. This information may be 
examined at the FAA, Office of the Regional Counsel, Southwest Region, 
2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137; or at the Office 
of the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Brian K. Murphy, Aviation Safety 
Engineer, ANE-150, 12 New England Executive Park, Burlington, MA 01803, 
telephone (781) 238-7739, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: On March 6, 2000, the FAA issued AD 2000-05-
16, Amendment 39-11626 (65 FR 13877, March 15, 2000). That AD for 
Sikorsky Model S-61 helicopters with pylon, part number (P/N) S6120-
76265-001 or S6120-76266-507, installed, requires inspecting and 
repairing or, if necessary, replacing certain web fittings and the 
fitting faying surfaces. The AD also requires making an entry on the 
log card or equivalent record. That action was prompted by the 
discovery of extensive cracking in the area of the web fitting. That 
condition, if not corrected, could result in structural failure of 
certain web fittings due to stress corrosion, subsequent structural 
failure of the tailboom and loss of control of the helicopter.
    Since the issuance of that AD, an operator notified the FAA of an 
error. That error is the reference in paragraph (a)(3) of the AD to 
paragraph 3.E. of the Accomplishment Instructions of Sikorsky Aircraft 
Corporation Alert Service Bulletin No. 61B20-33, dated September 3, 
1999 (ASB). Requiring paragraph 3.E. of the ASB in paragraph (a)(3) of 
the AD would inadvertently require conducting a major inspection within 
25 hours TIS, which is not intended. The Inspection Plan in Chart A of 
the ASB refers to paragraph 3.E., which specifies a major recurring 
inspection at 9000 flight hours or 4 years, whichever is less. That 
inspection is appropriately covered under paragraph (a)(6) of the AD, 
which requires entering on the log card or equivalent record the 
recurring inspection intervals in accordance with Chart A of the ASB.
    Since requiring the major inspection within 25 hours TIS is not 
required to correct the unsafe condition, this AD supersedes AD 2000-
05-16. This AD would correct the requirement that inadvertently 
requires conducting the major inspection in 25 hours TIS by removing 
the words ``and 3.E.'' from paragraph (a)(3) of the AD. The short

[[Page 40989]]

compliance time involved is required because the superseded AD is 
ambiguous and the previously described major inspection requiring 
unscheduled disassembly of the helicopter is impractical and 
unnecessary to maintain safety, and creates an undue burden on the 
public. Therefore, correcting paragraph (a)(3) by removing the words 
``and 3.E.'' is required and this AD must be issued immediately.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.
    The FAA estimates that 125 helicopters will be affected by this AD, 
that it will take approximately 115 work hours to accomplish the 
inspection and replacement of parts, and that the average labor rate is 
$60 per work hour. Required parts will cost approximately $75,000 per 
helicopter. Based on these figures, the total cost impact of the AD on 
U.S. operators is estimated to be $10,237,500 if the parts have to be 
replaced on the entire fleet.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications should identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their mailed 
comments submitted in response to this rule must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2000-SW-18-AD.'' The postcard will be date 
stamped and returned to the commenter.
    The regulations adopted herein will not have substantial direct 
effects 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, may be obtained from the Rules Docket at the 
location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing Amendment 39-11626 (65 FR 
13877, March 15, 2000) and by adding a new airworthiness directive 
(AD), Amendment 39-11805, to read as follows:

2000-13-06  Sikorsky Aircraft Corporation: Amendment 39-11805. 
Docket No. 2000-SW-18-AD. Supersedes AD 2000-05-16, Amendment 39-
11626, Docket No. 99-SW-61-AD.
    Applicability: Model S-61 helicopters with pylon, part number 
(P/N) S6120-76265-001 or S6120-76266-507, installed, certificated in 
any category.

    Note 1: This AD applies to each helicopter identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise modified, altered, or repaired in the area subject to the 
requirements of this AD. For helicopters that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (b) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent structural failure due to a crack or corrosion of 
pylon upper and lower hinge web fittings (web fittings), P/N S6120-
76261-012, -013 (upper) or S6120-76262-012, -013 (lower), and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Within 25 hours time-in-service (TIS),
    (1) Determine the alloy-temper of the web fittings in accordance 
with Sikorsky Aircraft Corporation Alert Service Bulletin No. 61B20-
33, dated September 3, 1999 (ASB), Accomplishment Instructions, 
paragraph 3.A.
    (2) Prepare the web fittings for inspection in accordance with 
the ASB Accomplishment Instructions, paragraph 3.B.
    (3) Inspect the web fitting in accordance with the ASB 
Inspection Plan, Chart A, and the Accomplishment Instructions, 
paragraphs 3.C. and 3.D. Nicks, scratches, corrosion pitting or 
prior rework beyond the limits specified in paragraph 3.C.(5) 
require approval by the FAA.
    (4) Repair or replace web fittings, as necessary, in accordance 
with the ASB Accomplishment Instructions, paragraph 3.C.(3) through 
(6). Nicks, scratches, corrosion pitting, or prior rework beyond the 
limits specified in paragraph 3.C.(5) require approval by the FAA.
    (5) If replacing an unairworthy web fitting with an airworthy 
web fitting, replace it in accordance with the ASB Accomplishment 
Instructions, paragraph 3.F., prior to further flight.
    (6) Create a log card for the pylon, if none exists. Make an 
entry on the log card or equivalent record implementing recurring 
inspection intervals in accordance with Chart A of the ASB.
    (b) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Boston Aircraft Certification 
Office, FAA. Operators shall submit their requests through an FAA 
Principal Maintenance Inspector, who may concur or comment and then 
send it to the Manager, Boston Aircraft Certification Office.


[[Page 40990]]


    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Boston Aircraft Certification Office.

    (c) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the helicopter to a location where 
the requirements of this AD can be accomplished.
    (d) The inspection, repair, and replacement shall be done in 
accordance with the Inspection Plan, Chart A, and the Accomplishment 
Instructions of Sikorsky Aircraft Corporation Alert Service Bulletin 
No. 61B20-33, dated September 3, 1999. This incorporation by 
reference of that document was approved previously by the Director 
of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51 as of March 30, 2000 (65 FR 13877, March 15, 2000). Copies 
may be obtained from Sikorsky Aircraft Corporation, Attn: Manager, 
Commercial Tech Support, 6900 Main Street, P. O. Box 9729, 
Stratford, Connecticut 06497-9129, phone (203) 386-7860, fax (203) 
386-4703. Copies may be inspected at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas; or at the Office of the Federal Register, 800 North Capitol 
Street, NW., suite 700, Washington, DC.
    (e) This amendment becomes effective on July 18, 2000.

    Issued in Fort Worth, Texas, on June 19, 2000.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-16356 Filed 6-30-00; 8:45 am]
BILLING CODE 4910-13-U


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