[Federal Register Volume 85, Number 239 (Friday, December 11, 2020)]
[Proposed Rules]
[Pages 79930-79934]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-27105]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 85, No. 239 / Friday, December 11, 2020 / 
Proposed Rules

[[Page 79930]]



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:
    <bullet> Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 <a href="/cdn-cgi/l/email-protection#412a33283235282f6f233320252d2438012720206f262e37"><span class="__cf_email__" data-cfemail="2e455c475d5a4740004c5c4f4a424b576e484f4f00494158">[email protected]</span></a>.

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 
<a href="/cdn-cgi/l/email-protection#670c150e14130e0949051506030b021e2701060649000811"><span class="__cf_email__" data-cfemail="ee859c879d9a8780c08c9c8f8a828b97ae888f8fc0898198">[email protected]</span></a>. 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

[[Page 79931]]

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:
    <bullet> 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.
    <bullet> 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.
    <bullet> Deactivating or removing any hoist that experiences 
partial peel out from service.
    <bullet> Reviewing records for cable load-testing that was 
previously performed, and depending on the findings, replacing the 
cable.
    <bullet> 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.
    <bullet> 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

[[Page 79932]]

$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

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):

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 installed on but not limited to the following:
    Note 1 to the introductory text of paragraph (a): The hoist P/N 
may be included 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 helicopters;
    (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 result 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.

[[Page 79933]]

    (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 
information 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:
[GRAPHIC] [TIFF OMITTED] TP11DE20.005

    (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:
[GRAPHIC] [TIFF OMITTED] TP11DE20.006

    (iii) For 500 and 600 lb rated hoists, install a placard with 
the information 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.
    (iv) For 500 and 600 lb rated hoists, install a placard with the 
information 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:
[GRAPHIC] [TIFF OMITTED] TP11DE20.007

    (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 assembly, 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 
conditioning and a hoist

[[Page 79934]]

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 <a href="/cdn-cgi/l/email-protection#f1b0a2b3dfa2b8a2dcb2b0b184859082df848592df929e9c"><span class="__cf_email__" data-cfemail="4f0e1c0d611c061c620c0e0f3a3b2e3c613a3b2c612c2022">[email protected]</span></a>; 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 
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.

(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 
<a href="/cdn-cgi/l/email-protection#f69d849f85829f98d8948497929a938fb6909797d8919980"><span class="__cf_email__" data-cfemail="e08b92899394898ece829281848c8599a0868181ce878f96">[email protected]</span></a>.
    (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 <a href="/cdn-cgi/l/email-protection#d5948697fb869c86f8969495a0a1b4a6fba0a1b6fbb6bab8"><span class="__cf_email__" data-cfemail="256476670b766c7608666465505144560b5051460b464a48">[email protected]</span></a>; 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 & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-27105 Filed 12-10-20; 8:45 am]
BILLING CODE P


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