[Federal Register Volume 67, Number 110 (Friday, June 7, 2002)]
[Rules and Regulations]
[Pages 39267-39269]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-14249]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-SW-10-AD; Amendment 39-12771; AD 2002-11-10]
RIN 2120-AA64


Airworthiness Directives; Sikorsky Model S-70A and S-70C 
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-70A and S-70C helicopters. That AD currently 
requires inspecting a certain part-numbered main landing gear drag beam 
(beam) for a crack, removing any cracked beam before further flight, 
and reducing the torque of the jackpad mounting bolt retention nut 
(nut) of each beam. This amendment contains the same actions but 
requires those actions for another beam part number (P/N). This 
amendment is prompted by the inadvertent omission in the current AD

[[Page 39268]]

of the additional beam that is susceptible to failure due to stress 
corrosion resulting from sustained excessive tensile stress due to 
excessive torque of the nut. The actions specified by this AD are 
intended to prevent excessive torque of the nut, failure of a beam, and 
subsequent loss of control of the helicopter during takeoff or landing.

DATES: Effective June 24, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before August 6, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2002-SW-10-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: [email protected].

FOR FURTHER INFORMATION CONTACT: Terry Fahr, Aviation Safety Engineer, 
Boston Aircraft Certification Office, 12 New England Executive Park, 
Burlington, MA 01803, telephone (781) 238-7155, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: On December 11, 2001, the FAA issued AD 
2001-25-08, Amendment 39-12561 (66 FR 65102, December 18, 2001), to 
require certain inspections of each beam,P/N 70250-32105, for a crack, 
removing any cracked beam before further flight, and reducing the 
torque of the nut on each beam. That action was prompted by the failure 
of a beam due to stress corrosion resulting from sustained excessive 
tensile stress due to excessive torque on the nut. That condition, if 
not corrected, could result in excessive torque of the nut, failure of 
a beam, and subsequent loss of control of the helicopter during takeoff 
or landing.
    Since the issuance of that AD, the FAA received a comment from the 
manufacturer stating that paragraph (a) of the AD should also apply to 
beam, P/N 70250-12105. The FAA agrees, and this superseding AD adds 
beam, P/N 70250-12105, to paragraph (a).
    This unsafe condition is likely to exist or develop on other 
helicopters of these same type designs. Therefore, this AD supersedes 
AD 2001-25-08 to contain the same requirements but to add the beam, P/N 
70250-12105, to paragraph (a) of this AD.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability and structural integrity of the helicopter. Therefore, 
within 30 hours time-in-service, the following actions are required, 
and this AD must be issued immediately:
     Visually inspect each beam for a crack.
     If a crack is found, remove the beam before further 
flight.
     If a crack is suspected, dye-penetrant inspect the beam, 
and if a crack is found, remove the beam before further flight.
     If no crack is found, reduce the torque on the nut.
    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 3 helicopters currently type certificated in 
the United States (U.S.) will be affected by this AD, that it will take 
approximately 4 work hours to inspect the beam, to reduce the torque on 
each nut, and to replace a cracked beam. The average labor rate is $60 
per work hour. Required parts will cost approximately $18,600 per beam. 
Based on these figures, the total cost impact of the AD on U.S. 
operators is estimated to be $56,520, assuming you replace one beam on 
each U.S. helicopter and assuming that no other helicopter listed in 
the ``applicability'' will be type certificated in the U.S.

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 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 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. 2002-SW-10-AD.'' The postcard will be date stamped and 
returned to the commenter.
    The regulations adopted herein 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. 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, 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 39-12561 (66 FR 
65102, December 18, 2001), and by adding a new airworthiness directive 
(AD), Amendment 39-12771, to read as follows:


[[Page 39269]]


2002-11-10  Sikorsky Aircraft Corporation: Amendment 39-12771. 
Docket No. 2002-SW-10-AD. Supersedes AD 2001-25-08, Amendment 39-
12561, Docket No. 2001-SW-18-AD.

    Applicability: Model S-70A helicopters, serial numbers (S/N) 
700029, 701129, 701322, 701325, 701327, 701329, 701331, 701333, 
701592, 701593, 701594, 701595, 701613, 701614, 701825, 701835, 
702127, and 702129, and Model S-70C helicopters, S/N 70583, 70785, 
70788, 70792, 70793, 70794, 70797, 70798, 70799, 70800, 70811, 
70812, 70813, 70830, 70831, 70836, 70837, 70848, 70855, 70856, 
70867, 70868, 70879, 70884, 70892, 70910, 70918, 70927, 70928, 
70929, 70949, 70950, 70951, 70954, 70957, 70958, 70959, 70965, 
70966, and 701029, 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 (c) 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 within 30 hours time-in-service, unless 
accomplished previously.
    To prevent excessive torque on a jackpad mounting bolt retention 
nut (nut), failure of a main landing gear drag beam (beam), and 
subsequent loss of control of the helicopter during takeoff or 
landing, accomplish the following:
    (a) With jackpad installed, using a 10X or higher magnifying 
glass, visually inspect each beam, part number (P/N) 70250-12105 or 
70250-32105, for a crack at a 3.0-inch radius around the upper and 
lower jackpad holes.
    (1) If a crack is found, remove the beam.
    (2) If a crack is suspected, dye-penetrant inspect the beam, and 
if a crack is found, remove the beam.

    Note 2: Temporary Revision No. 19 of Sikorsky Aircraft Model S-
70 Maintenance Manual, dated January 23, 2001, pertains to the 
subject of this AD.


    (b) If a crack is not found while accomplishing the requirements 
of paragraph (a) of this AD, retorque the nut, P/N MS21245-L12, on 
each beam as follows:
    (1) Restrain the jackpad and rotate the nut counterclockwise to 
release the torque on the nut. If movement of the jackpad occurs, 
remove and replace the sealant from the lower surface of the 
jackpad/beam interface.
    (2) Retorque the nut to 45-50 ft-lbs.
    (3) Apply sealant to the nut and the immediate area.
    (4) After sealant has dried, touch up the paint as required.
    (5) After the paint has dried, apply a slippage mark (of a 
contrasting color) to the nut as follows:
    (i) Wipe the area to be marked with a clean-lint-free cloth.
    (ii) Apply F1000 Sentry Seal, or equivalent, with a width of 
approximately one half the diameter of the nut (to a maximum width 
of \3/16\ inch) and extending a minimum of \1/2\ inch on the base 
part (or to the edge of the part, whichever is smaller).

    Note 3: Sikorsky Alert Service Bulletin No. 70-03-2, dated July 
26, 1999, pertains to the subject of this AD.


    (c) 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 Inspector, who may concur or comment and then send it to 
the Manager, Boston Aircraft Certification Office.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Boston Aircraft Certification Office.


    (d) Special flight permits may be issued in accordance with 14 
CFR 21.197 and 21.199 to operate the helicopter to a location where 
the requirements of this AD can be accomplished.
    (e) This amendment becomes effective on June 24, 2002.

    Issued in Fort Worth, Texas, on May 28, 2002.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-14249 Filed 6-6-02; 8:45 am]
BILLING CODE 4910-13-P