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.

Proposed Rules Federal Register

79930 

Vol. 85, No. 239 

Friday, December 11, 2020 

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 externallymounted 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 externallymounted 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 


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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 loadtesting 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° 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 loadtested 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 


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$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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 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 partnumbered 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. 


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(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: 

(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: 

(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: 

(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 


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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 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 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 & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2020–27105 Filed 12–10–20; 8:45 am] 

BILLING CODE P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2020–0727; Airspace 

Docket No. 20–ACE–18] 

RIN 2120–AA66 

Proposed Amendment of Class E 

Airspace; Cambridge NE 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

amend Class E airspace, extending 

upward from 700 feet above the surface. 

This action also proposes several 

administrative corrections to the 

airspace’s legal description. This action 

would ensure the safety and 

management of instrument flight rules 

(IFR) operations at the airport. 

DATES: Comments must be received on 

or before January 25, 2021. 

ADDRESSES: Send comments on this 

proposal to the U.S. Department of 

Transportation, Docket Operations, 1200 

New Jersey Avenue SE, West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590; telephone: 1– 

800–647–5527, or (202) 366–9826. You 

must identify FAA Docket No. FAA– 

2020–0727; Airspace Docket No. 20– 

ACE–18, at the beginning of your 

comments. You may also submit 

comments through the internet at 

https://www.regulations.gov. 

FAA Order 7400.11E, Airspace 

Designations and Reporting Points, and 

subsequent amendments can be viewed 

online at https://www.faa.gov/air_

traffic/publications/. For further 

information, you can contact the 

Airspace Policy Group, Federal Aviation 

Administration, 800 Independence 

Avenue SW, Washington, DC 20591; 

telephone: (202) 267–8783. The Order is 

also available for inspection at the 

National Archives and Records 

Administration (NARA). For 

information on the availability of FAA 

Order 7400.11E at NARA, email 

fedreg.legal@nara.gov or go to https://

www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

FOR FURTHER INFORMATION CONTACT: 

Matthew Van Der Wal, Federal Aviation 

Administration, Western Service Center, 

Operations Support Group, 2200 S 

216th Street, Des Moines, WA 98198; 

telephone (206) 231–3695. 

SUPPLEMENTARY INFORMATION: 


jbell on DSKJLSW7X2PROD with PROPOSALS