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PROPOSED AD GOODRICH EXTERNALLY-MOUNTED HOIST ASSEMBLIES: Docket No. FAA-2020-1120; Product Identifier 2019-SW-056-AD.
(a) APPLICABILITY

    This AD applies to helicopters, certificated in any category,  with an
    externally-mounted hoist assembly (hoist) with a part number (P/N)  or
    base P/N listed under the Hoist  Family column in Table 1 of  Goodrich
    Alert Service Bulletin No. 44301-10-18, Revision 6,  dated October 10,
    2016 (ASB 44301-10-18 Rev 6), installed.  An affected hoist may be in-
    stalled on but not limited to the following:

Note 1 to the introductory text of paragraph (a): The hoist P/N may be in-
cluded as a component of a different part-numbered kit.

(1) Airbus  Helicopters  (previously  Eurocopter  France)   Model  AS332L,
    AS332L1, AS332L2, AS350B2, AS350B3, AS365N3, and EC225LP helicopters;

(2) Airbus  Helicopters  Deutschland  GmbH  (AHD)  (previously  Eurocopter
    Deutschland GmbH)  Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1,
    EC135T2, EC135T2+, EC135T3, MBB-BK 117 C-2 and MBB-BK 117 D-2 helicop-
    ters;

(3) Bell Textron Canada Limited (previously Bell Helicopter Textron Canada
    Limited) Model 429 and 430 helicopters;

(4) Bell Textron Inc. (previously Bell Helicopter Textron Inc) Model 205A,
    205A-1, 205B, 212, 412, 412CF, and 412EP helicopters;

(5) Leonardo S.p.a. (previously Finmeccanica S.p.A., AgustaWestland S.p.A)
    Model A109, A109A,  A109A II,  A109C,  A109E,  A109K2,  A109S,  AB139,
    AB412, AB412 EP, AW109SP, and AW139, helicopters;

(6) MD Helicopters, Inc. (MDHI) Model MD900 helicopters;

(7) Transport and restricted category helicopters, originally manufactured
    by  Sikorsky Aircraft Corporation,  Models S-61A, S-61L, S-61N, S-76A,
    S-76B, S-76C, S-76D, and S-92A; and

(8) Restricted  category  Model  HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E,
    UH-1F, UH-1H, UH-1L, and UH-1P helicopters.

(b) UNSAFE CONDITION

    This AD defines the unsafe condition  as failure of the hoist overload
    clutch resulting in an in-flight failure of the hoist, which could re-
    sult in injury to a person being lifted.

(c) COMMENTS DUE DATE

    The FAA must receive comments by January 25, 2021.

(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) For a hoist  without the number "4" as the first digit  of  its serial
    number (S/N), before further flight:

(i) For hoists that use operating hours to monitor hoist operation, within
    12 months  after the  effective date  of this  AD or  before the hoist
    accumulates 55 hoist operating hours, whichever occurs first,  replace
    the hoist. For purposes of this AD, hoist operating hours are  counted
    anytime the hoist motor is operating.

(ii) For hoists that use hoist cycles (cycles) to monitor hoist operation,
     within 12 months after  the effective date of  this AD or before  the
     hoist accumulates 1,200 cycles,  whichever occurs first, replace  the
     hoist. For purposes of this AD, a cycle is counted anytime the  cable
     is extended and then retracted a minimum of 16 feet (5 meters) during
     flight or on the ground, with or without a load.

(iii) For hoists that use hoist lifts (lifts)  to monitor hoist operation,
      within 12 months after the effective  date of this AD or before  the
      hoist accumulates 1,600 lifts,  whichever occurs first, replace  the
      hoist. For purposes of this AD, a lift is counted anytime the  cable
      is unreeled or recovered or both  with a load attached to the  hook,
      regardless of the length of the cable that is deployed or recovered.
      An unreeling or recovery  of the cable with  no load on the  hook is
      not  a  lift. If  a  load is  applied  for half  an  operation (i.e.
      unreeling or recovery), it must be counted as one lift.

(2) For all hoists identified in the introductory text of paragraph (a) of
    this  AD,  before  further flight,  install  placards  and revise  the
    existing  Rotorcraft  Flight  Manual  (RFM)  for  your  helicopter  by
    inserting  a copy  of this  AD  or  by making  pen-and-ink changes  in
    Section  2,  Limitations,  of  the RFM  Supplement  for  the  hoist as
    follows:

(i) For 500 pound (lb) rated hoists,  install a placard  with the informa-
    tion in Figure 1 to paragraph (e)(2)(i) of this AD in full view of the
    hoist  operator  and add  the  information in  Figure  1 to  paragraph
    (e)(2)(i) of this AD to the existing RFM for your helicopter:

                        FIGURE 1 TO PARAGRAPH (E)(2)(I)
    ______________________________________________________________________
                              500 lb Rated Hoist

        OAT at or above 32F (0C): Maximum hoist load 450 lbs (204 kg)
     OAT between -4F (-20C) and 32F (0C): Maximum hoist load 400 lbs
                                    (181 kg)
    ______________________________________________________________________

(ii) For  600 lb rated hoists,  install a placard  with the information in
     Figure 2 to paragraph (e)(2)(ii) of this AD in full view of the hoist
     operator and add the information  in Figure 2 to paragraph (e)(2)(ii)
     of this AD to the existing RFM for your helicopter:

                       FIGURE 2 TO PARAGRAPH (E)(2)(II)
    ______________________________________________________________________
                              600 lb Rated Hoist

       OAT at or above 32F (0C): Maximum hoist load 550 lbs (249 kg)
     OAT between -4F (-20C) and 32F (0C): Maximum hoist load 500 lbs
                                   (227 kg)
    ______________________________________________________________________

(iii) For 500 and 600 lb rated hoists, install a placard with the informa-
      tion in Figure 3 to paragraph (e)(2)(iii) of this AD in full view of
      the  pilot  and  add  the  information  in  Figure  3  to  paragraph
      (e)(2)(iii) of this AD to the existing RFM for your helicopter.

                       FIGURE 3 TO PARAGRAPH (E)(2)(III)
    ______________________________________________________________________
                                Hoist Operations

      Warning: Excessive maneuvering with extended cable and load on the
                  hook may cause uncommanded peel out of the cable.

                     Maximum sustained bank angle in turn is 20
    ______________________________________________________________________

(iv) For 500 and 600 lb rated hoists,  install a placard with the informa-
     tion in Figure 4 to paragraph  (e)(2)(iv) of this AD in full  view of
     the pilot and add the information in Figure 4 to paragraph (e)(2)(iv)
     of this AD to the existing RFM for your helicopter:

                       FIGURE 4 TO PARAGRAPH (E)(2)(IV)
    ______________________________________________________________________
                           Hoist - Partial Peel Out

      If a partial peel out occurs, before next flight, cease using the
    hoist. A partial peel out occurs when 20 inches (0.5 meter) or more of
      the hoist cable reels off of the hoist cable drum in one overload
                             clutch slip incident.
    ______________________________________________________________________

(3) For all hoists identified in the introductory text of paragraph (a) of
    this AD, as of  the effective date of  this AD, if a  partial peel out
    occurs, deactivate  or remove  the hoist  from service  before further
    flight. For purposes  of this AD,  a partial peel  out occurs when  20
    inches (0.5 meter) or more of  the hoist cable reels off of  the hoist
    cable drum in one overload clutch slip incident.

(4) For all hoists identified in the introductory text of paragraph (a) of
    this AD, within 30  days after the effective  date of this AD,  review
    the helicopter's hoist slip load  test records. If the cable  was load
    -tested at more than 1,500 lbs  or at an unknown weight during  one or
    more cable pulls, replace the cable with an airworthy cable before the
    next hoist operation.

(5) For all hoists identified in the introductory text of paragraph (a) of
    this AD,  within 30  days after  the effective  date of  this AD,  and
    thereafter at  intervals not  to exceed  6 months,  400 lifts,  or 300
    cycles, whichever occurs first:

(i) Visually inspect the first 18 inches (45 cm)  of  the  cable  from the
    hook assembly for broken wires and necked down sections. If there is a
    broken  wire  or  necked  down  section,  replace  the  cable  with an
    airworthy cable before further flight.

(ii) Within the first 18 inches (45 cm) of the cable  from the hook assem-
     bly,  measure the diameter of the cable at the most necked down area.
     If the diameter measurement is less than 0.185 inch (4.7 mm), replace
     the cable with an airworthy cable before further flight.

(iii) Using load check tool P/N 49900-889-104,  perform a cable condition-
      ing  and  a  hoist slip  load test  by following  the Accomplishment
      Instructions, paragraphs 3.C.(1) through 3.C.(3)(g) of ASB  44301-10
      -18 Rev 6. If the average of  the five test values is less than  the
      limit shown in Table 2 for 600 lb rated hoists or Table 3 for 500 lb
      rated hoists of ASB 44301-10-18 Rev 6, remove the hoist from service
      before further flight.

(iv) Visually inspect the first 30 feet (10 meters) of the cable  from the
     hook assembly  for broken  wires, necked  down sections,  kinks, bird
     -caging, flattened  areas, abrasion,  and gouging.  It is permissible
     for the cable to have a slight curve immediately after performing the
     hoist slip load test. If there is a broken wire, necked down section,
     kink,  or any  bird-caging;  or  if there  is a  flattened area,  any
     abrasion, or a gouge that exceeds allowable limits, replace the cable
     with an airworthy cable before further flight.

(v) Repeat the actions specified in paragraphs (e)(5)(i) and (ii)  of this
    AD. If  there is  a broken  wire or  necked down  section or the cable
    diameter measurement  is less  than 0.185  inch (4.7  mm), replace the
    cable with an airworthy cable before further flight.

(6) Within 30 days  after accomplishing  the hoist slip load test,  report
    the information requested in Appendix 1 to this AD by email to ASB.SIS
    -CA@utas.utc.com;  or  mail  to Goodrich,  Collins Aerospace;  2727 E.
    Imperial Hwy., Brea, CA 92821.

(7) As of the effective date of this AD,  do not install  as a replacement
    part or as an original installation an externally-mounted hoist with a
    P/N identified in the introductory text  of  paragraph (a)  of this AD
    unless it has an improved overload clutch assembly with the number "4"
    as the first digit of the S/N.

(f) PAPERWORK REDUCTION ACT BURDEN STATEMENT

    A federal agency may not conduct or sponsor,  and  a person is not re-
    quired to respond to, nor shall  a person be subject to a  penalty for
    failure to  comply with  a collection  of information  subject to  the
    requirements of the Paperwork Reduction Act unless that collection  of
    information displays  a currently  valid OMB  Control Number.  The OMB
    Control Number  for this  information collection  is 2120-0056. Public
    reporting  for  this  collection of  information  is  estimated to  be
    approximately 0.25 hour per response, including the time for reviewing
    instructions,   searching   existing  data   sources,   gathering  and
    maintaining  the  data  needed,  and  completing  and  reviewing   the
    collection  of  information.  All  responses  to  this  collection  of
    information  are  mandatory.  Send  comments  regarding  this   burden
    estimate  or  any  other aspect  of  this  collection of  information,
    including  suggestions  for  reducing  this  burden  to:   Information
    Collection Clearance Officer,  Federal Aviation Administration,  10101
    Hillwood Parkway, Fort Worth, TX 76177-1524.

(g) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The Manager, International Validation Branch,  FAA,  may approve AMOCs
    for this AD. Send your proposal to Kristi Bradley, Aerospace Engineer,
    General Aviation & Rotorcraft Section, International Validation Branch
    FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone 817-222-5110
    email kristin.bradley@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate
    or under 14 CFR part 91,  subpart K, the FAA suggests 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.

(h) ADDITIONAL INFORMATION

    The subject of this AD is addressed  in European Union Aviation Safety
    Agency (EASA) AD No. 2015-0226R5, Revision 5, dated July 23, 2020. You
    may view the EASA AD on the internet at https://www.regulations.gov in
    the AD Docket.

(i) SUBJECT

    Joint Aircraft Service Component (JASC) Code:  2500,  Cabin Equipment/
    Furnishings.

APPENDIX 1 TO AD ####-##-##

HOIST SLIP LOAD TEST RESULTS (SAMPLE FORMAT)

Provide the following information by email to ASB.SIS-CA@utas.utc.com;  or
mail to Goodrich, Collins Aerospace; 2727 E. Imperial Hwy, Brea, CA 92821.

Helicopter Owner/Operator Name:
Email Address:
Telephone Number:
Helicopter Model and Serial Number:
Hoist Part Number:
Hoist Serial Number:
Time since Last Hoist Overhaul (months):
Hoist Operating Hours:
Hoist Cycles:
Hoist Lifts:
Date and Location Test was Accomplished:
Point of Contact for Additional Information:
Air Temperature:
Gearbox Lubricant:
Hoist Slip Load Test Value 1:
Hoist Slip Load Test Value 2:
Hoist Slip Load Test Value 3:
Hoist Slip Load Test Value 4:
Hoist Slip Load Test Value 5:
Hoist Slip Load Test Averaged Test Value:
Any notes or comments:

Issued on December 4, 2020. Lance T Gant, Director, Compliance & Airworth-
iness Division, Aircraft Certification Service.

DATES: The FAA must receive comments  on this proposed AD  by  January 25,
2021.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-1120; Product Identifier 2019-SW-056-AD]
RIN 2120-AA64

Airworthiness Directives; Goodrich Externally-Mounted Hoist Assemblies

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for various model helicopters with certain part-numbered Goodrich
externally-mounted hoist assemblies (hoists) installed. This proposed
AD would require replacing unmodified hoists, installing placards,
revising the existing Rotorcraft Flight Manual (RFM) for your
helicopter, deactivating or removing a hoist if a partial peel out
occurs, reviewing the helicopter's hoist slip load test records,
repetitively inspecting the hoist cable and overload clutch (clutch),
and reporting information to the FAA. This proposed AD would also
require establishing operating limitations on the hoist and prohibit
installing an unmodified hoist. This proposed AD was prompted by hoists
failing lower load limit inspections. The actions of this proposed AD
are intended to address an unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by January 25,
2021.

ADDRESSES: You may send comments by any of the following methods:

Federal eRulemaking Docket: Go to https://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 https://www.regulations.
gov by searching for and locating Docket No. FAA-2020-1120;
or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this proposed AD, the European Union Aviation Safety Agency (EASA) AD,
any comments received, and other information. The street address for
Docket Operations is listed above. Comments will be available in the AD
docket shortly after receipt.

For service information identified in this proposed rule, contact
Collins Aerospace; 2727 E Imperial Hwy., Brea, CA 92821; telephone 714-
984-1461. You may view 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: Kristi Bradley, Aerospace Engineer,
General Aviation & Rotorcraft Section, International Validation Branch,
FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-
5110; email kristin.bradley@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include "Docket No. FAA-2020-1120; Product Identifier
2019-SW-056-AD" at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this proposal because of those comments.

Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
http://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this proposal.

Confidential Business Information

CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as "PROPIN." The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to
Kristi Bradley, Aerospace Engineer, General Aviation & Rotorcraft
Section, International Validation Branch, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone 817-222-5110; email
kristin.bradley@faa.gov. Any comments that the FAA receives which are
not specifically designated as CBI will be placed in the public docket
for this rulemaking.

Discussion

EASA, which is the Technical Agent for the Member States of the
European Union, has issued a series of ADs, the most recent being EASA
AD No. 2015-0226R5, Revision 5, dated July 23, 2020 (EASA AD 2015-
0226R5), to correct an unsafe condition for various model helicopters
with a Goodrich externally-mounted hoist that has one of the following
part numbers (P/Ns) or base P/Ns installed: 42315, 42325, 44301-10-1,
44301-10-2, 44301-10-4, 44301-10-5, 44301-10-6, 44301-10-7, 44301-10-8,
44301-10-9, 44301-10-10, 44301-10-11, 44311, 44312, 44314, 44315,
44316, or 44318. These hoists have a common overload clutch design.
EASA advises of an initial incident of a rescue hoist containing a
dummy test load of 552 lbs. that reeled-out without command of the
operator and impacted the ground during a maintenance check flight.
Examination of the hoist determined that the overload clutch had failed.
EASA states that this condition, if not detected and corrected, could lead
to further cases of in-flight loss of the hoist load, possibly resulting
in injury to persons on the ground or in a hoisting accident.

EASA also determined that some versions of the existing clutch had
not been approved for aircraft use. EASA advises that Goodrich
developed a new overload clutch with improved process control to
mitigate some of the factors resulting in the degraded clutch
performance. EASA's series of ADs were issued to adjust compliance
intervals and replacement times, and include revised service
information. EASA AD 2015-0226R5 was prompted by a major change
approval for Leonardo S.p.a. Model AW109SP helicopters that allows a
longer overhaul interval for hoists with the new overload clutch
installed.

Accordingly, EASA AD 2015-0226R5 requires a records review to
determine if the cable has exceeded the allowable limit in previous
load testing, a repetitive load check and test of the clutch slip
value, removal or deactivation of a hoist that cannot be tested due to
lack of approved instructions, replacement of the old clutch P/N with a
new clutch developed by Goodrich to mitigate some of the factors
resulting in clutch degradation, periodic replacement of the hoist,
reduction of the maximum allowable load on the hoist, addition of
operational limitations to the RFM, and replacement of the hoist after
a partial peel out. EASA AD 2015-0226R5 also prohibits the installation
of a replacement cable that has exceeded the allowable limit in
previous load testing. EASA considers AD 2015-0226R5 to be interim
action and advises further AD action may follow.

FAA's Determination

Affected helicopters include helicopters that have been approved by
the aviation authorities of Canada, Italy, France, and Germany and are
approved for operation in the United States. Pursuant to the FAA's
bilateral agreement with the European Union, EASA has notified the FAA
about the unsafe condition described in its AD. The FAA is proposing
this AD after evaluating all known relevant information and determining
that an unsafe condition is likely to exist or develop on other
helicopters.

Related Service Information Under 1 CFR Part 51

The FAA reviewed Goodrich Alert Service Bulletin (ASB) 44301-10-18,
Revision 6, dated October 10, 2016 (ASB 44301-10-18, Rev 6), which
specifies maximum hoist load limitations with respect to ambient
temperature and describes actions and conditions that could reduce the
capacity of the clutch. This service information also specifies
procedures for inspecting the cable and inspecting the clutch by
performing a cable conditioning lift and a hoist slip load test.

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:

Replacing any hoist without a "4" as the first digit of
its serial number (S/N) within 12 months after the effective date of
this AD or before the hoist accumulates 55 operating hours, 1,200 hoist
cycles (cycles), or 1,600 hoist lifts (lifts), whichever occurs first.

Installing placards and revising the existing RFM for your
helicopter to add maximum hoist load limitations, an excessive
maneuvering warning, a maximum sustained bank angle in turn, and a
prohibition on operating the hoist in the event of a partial peel out.

Deactivating or removing any hoist that experiences
partial peel out from service.

Reviewing records for cable load-testing that was
previously performed, and depending on the findings, replacing the
cable.

Repetitively inspecting the cable, inspecting the clutch
by performing a cable conditioning lift and hoist slip load test,
inspecting the cable a second time, reporting certain information to
the FAA, and depending on these inspection outcomes, replacing the
cable or removing the hoist from service.

This proposed AD would also prohibit installing an
affected replacement or original installation hoist that has not been
re-identified to indicate a new improved clutch assembly.

Installation of a hoist with an improved overload clutch assembly,
which is indicated by having a "4" as the first digit of its S/N,
would not terminate the actions required by this proposed AD.

Differences Between This Proposed AD and the EASA AD

The EASA AD requires repetitively replacing the hoist with a
modified hoist, whereas this proposed AD would not require repetitive
replacement once a modified hoist with the improved clutch assembly is
installed. The EASA AD requires adding a placard or operational
limitation to the RFM warning that exceeding 15[deg] of lateral
pendulum angle/helicopter vertical axis can lead to clutch slippage,
and this proposed AD would not. The EASA AD requires adding an
operating limitation to the RFM limiting the number of persons who can
be hoisted, whereas this proposed AD would not. This proposed AD would
require replacing the cable before the next hoist operation if a cable
has previously been load-tested at more than 1,500 lbs or at an unknown
weight during at least one cable pull, while the EASA AD requires this
replacement during multiple cable pulls. This proposed AD would require
visually inspecting and measuring the diameter of the cable before and
after performing a cable conditioning and a hoist slip load test,
whereas the EASA AD does not. This proposed AD would require performing
the cable conditioning and hoist slip load test within 30 days and
thereafter at intervals not to exceed 6 months, 400 lifts, or 300
cycles. The EASA AD specifies performing the hoist slip load test
according to the compliance time of the design approval holder instead.
After the installation (not reinstallation) of a modified hoist, the
EASA AD requires performing an initial hoist load check/test prior to
hoisting operation, whereas this proposed AD would not.

Interim Action

The FAA considers this proposed AD to be an interim action. The
inspection reports that would be required by this proposed AD will
enable better insight into the condition of the hoists, and eventually
to develop final action to address the unsafe condition. Once final
action has been identified, the FAA might consider further rulemaking.

Costs of Compliance

The FAA estimates that this proposed AD affects 2,911 helicopters
of U.S. Registry. Labor rates are estimated at $85 per work-hour. Based
on these numbers, the FAA estimates that operators may incur the
following costs in order to comply with this proposed AD.

Replacing a hoist would take about 8 work-hours and parts would
cost about $200,000 for an estimated cost of $200,680.

Revising the existing RFM for your helicopter and installing
placards would take about 0.5 work-hour for an estimated cost of $43
per helicopter and $125,173 for the U.S. fleet.

Deactivating or removing a hoist that experiences partial peel out
would take about 2 work-hours for an estimated cost of $170.

Reviewing records would take about 0.5 work-hour for an estimated
cost of $43 per helicopter and $125,173 for the U.S. fleet.

Inspecting the cable and performing a cable conditioning lift and
hoist slip load test would take about 2 work-hours for an estimated
cost of $170 per helicopter and $494,870 for the U.S. fleet per
inspection cycle. Reporting the hoist slip load test information would
take about 0.25 work-hour for a cost of $21 per helicopter and $61,131
for the U.S. fleet per reporting cycle.

Replacing the cable would take about 3 work-hours and parts would
cost about $3,150 for a total replacement cost of $3,405.

Paperwork Reduction Act

A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a currently valid OMB Control Number. The OMB
Control Number for this information collection is 2120-0056. Public
reporting for this collection of information is estimated to be
approximately 0.25 hour per response, including the time for reviewing
instructions, searching existing data sources, gathering and
maintaining the data needed, and completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Send comments regarding this burden estimate
or any other aspect of this collection of information, including
suggestions for reducing this burden to: Information Collection
Clearance Officer, Federal Aviation Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177-1524.

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.

The FAA is 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

The FAA 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 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. Will not affect intrastate aviation in Alaska, and

3. 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.

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

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. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):