2358 Federal Register / Vol. 83, No. 11 / Wednesday, January 17, 2018 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0895; Product 

Identifier 2017–SW–048–AD; Amendment 

39–19161; AD 2018–02–08] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Bell 

Helicopter Textron (Bell) Model 204B, 

205A, and 205A–1 helicopters with a 

Helicopter Technology Company (HTC) 

main rotor (M/R) blade installed. This 

AD requires cleaning and visually 

inspecting the M/R blades, and 

depending on the outcome of the 

inspection, repairing or replacing the M/ 

R blades. This AD is prompted by a 

report of an M/R blade with a fatigue 

crack in the grip plate and doublers at 

the blade retention bolt hole. The 

actions of this AD are intended to 

correct an unsafe condition on these 

products. 

DATES: This AD becomes effective 

February 1, 2018. 

We must receive comments on this 

AD by March 19, 2018. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://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 http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0895; 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 AD, the 

economic evaluation, any comments 

received, and other information. The 

street address for Docket Operations 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

For service information identified in 

this final rule, contact Bell Helicopter 

Textron, Inc., P.O. Box 482, Fort Worth, 

TX 76101; telephone (817) 280–3391; 

fax (817) 280–6466; or at http://

www.bellcustomer.com/files/. You may 

review 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: 

Galib Abumeri, Aerospace Engineer 

(Structures), Airframe Section, Los 

Angeles ACO Branch, Compliance and 

Airworthiness Division, FAA, 3960 

Paramount Blvd., Lakewood, California 

90712; telephone 562–627–5324; email 

galib.abumeri@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. We will file 

in the docket all comments that we 

receive, as well as a report summarizing 

each substantive public contact with 

FAA personnel concerning this 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

We are adopting a new AD for Bell 

204B, 205A and 205A–1 helicopters 

with an HTC M/R blade part number (P/ 

N) 204P2100–101 installed. This AD 

requires repetitive inspections of the 

exposed areas of the lower grip pad and 

upper and lower grip plates of each M/ 

R blade for a crack, corrosion, an edge 

void, loose or damaged adhesive 

squeeze-out, and an edge delamination. 

The actions of this AD are the same 

as those required by AD 2016–22–07 (81 

FR 74285, October 26, 2016), which 

applies to Bell Model 204B, 205A and 

205A–1 helicopters with an M/R blade 

P/N 204–011–200–001 or P/N 204–011– 

250-(all dash numbers) installed. AD 

2016–22–07 was prompted by a report 

of an M/R blade with multiple fatigue 

cracks around the retention bolt hole. 

This AD is prompted by a report that 

during a ground inspection, a crack was 

discovered in the grip plate and 

doublers at the blade retention bolt hole 

of a UH–1B helicopter model. The 

blade, which HTC produced for 

restricted category and commercial 

model helicopters, had 926 hours TIS 

and is of the same design as the M/R 

blades in AD 2016–22–07. We are 

issuing this AD to detect or prevent a 

crack, which could lead to failure of an 

M/R blade and subsequent loss of 

helicopter control. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of these same 

type designs. 

Related Service Information 

HTC has issued Service Notice No. 

204–2100–1 on July 5, 2017, for affected 

helicopters with M/R blade P/N 

204P2100–101, serial numbers A099 

through A119 installed. This service 

notice specifies cleaning and visually 

inspecting the M/R blades and 

depending on the outcome, repairing or 

replacing the blades in accordance with 

AD 2016–23–09. 

We also reviewed Bell Helicopter 

Alert Service Bulletin (ASB) No. UH– 

1H–13–09, dated January 14, 2013, for 

the Model UH–1H helicopter. ASB No. 

UH–1H–13–09 specifies a one-time 

visual inspection, within 10 hours timein-service (TIS), of the lower grip pad 

and upper and lower grip plates for 

cracks, edge voids, and loose or 

damaged adhesive squeeze-out. ASB No. 

UH–1H–13–09 also specifies a repetitive 

and more detailed visual inspection, 

daily and at every 150 hours TIS, of the 

lower grip pad, upper and lower grip 

plates, and all upper and the lower 

doublers for cracks, corrosion, edge 

voids, and loose or damaged adhesive 

squeeze-out. 

Lastly, we reviewed Bell Helicopter 

ASB No. 204–75–1 for Model 204B 

helicopters and ASB No. 205–75–5 for 

Model 205A–1 helicopters, both 

Revision C and both dated April 25, 

1979. ASB No. 204–75–1 and ASB No. 

205–75–5 specify visually inspecting 


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Federal Register / Vol. 83, No. 11 / Wednesday, January 17, 2018 / Rules and Regulations 2359 

the M/R blades during each daily 

inspection. ASB No. 204–75–1 and ASB 

No. 205–75–5 also provide instructions 

for repetitively inspecting the blades 

every 1,000 hours of operation or every 

12 months, whichever occurs first. 

AD Requirements 

This AD requires within 25 hours 

time-in-service (TIS) or 2 weeks, 

whichever occurs first, and thereafter at 

intervals not to exceed 25 hours TIS or 

2 weeks, whichever occurs first, 

cleaning the upper and lower exposed 

surfaces of each M/R blade from an area 

starting at the butt end of the blade to 

three inches outboard of the doublers. 

Using a 3X or higher power magnifying 

glass and a light, this AD also requires 

visually inspecting various M/R blade 

parts for a crack or corrosion. If there is 

a crack, corrosion, an edge void, loose 

or damaged adhesive squeeze-out, or an 

edge delamination, before further flight, 

this AD requires repairing the M/R 

blade or replacing it with an airworthy 

M/R blade, depending on whether the 

condition is within maximum repair 

damage limits. 

This AD also requires reporting 

information about any cracks found 

during the inspection to the FAA within 

10 days. 

Differences Between This AD and the 

Service Information 

This AD requires all inspections every 

25 hours TIS or 2 weeks, whichever 

occurs first. ASB 204–75–1 and ASB 

205–75–5 call for daily visual 

inspections, and inspections, rework, 

and refinishing every 1,000 hours TIS or 

12 months, whichever occurs first. The 

service information applies to Bell M/R 

blade P/N 204–011–250. This AD 

applies to HTC M/R blade P/N 

204P2100–101. 

Interim Action 

We consider this AD to be an interim 

action. The notification of a crack in the 

M/R blade that is required by this AD 

may enable us to obtain better insight 

into the cause of the M/R blade 

cracking. This information may help us 

develop additional action to address 

this unsafe condition. Once this action 

is developed, approved, and available, 

we might consider additional 

rulemaking. 

Costs of Compliance 

We estimate that this AD affects 10 

helicopters of U.S. Registry and that 

labor costs average $85 per work-hour. 

Based on these estimates, we expect the 

following costs: 

• Cleaning and performing all 

inspections of a set of M/R blades (2 per 

helicopter) requires 0.5 work-hour for a 

cost of $43 per helicopter and $430 for 

the U.S. fleet per inspection cycle. 

• Replacing an M/R blade requires 12 

work-hours and parts cost $86,000 for a 

total cost of $87,020 per blade. 

• Reporting the inspection results 

required by this AD will require about 

0.5 work-hour for a cost of $43 per 

helicopter and $430 for the U.S. fleet 

per report. 

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 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 current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting required by this 

AD is mandatory. Comments concerning 

the accuracy of this burden and 

suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW, Washington, 

DC 20591. ATTN: Information 

Collection Clearance Officer, AES–200. 

FAA’s Justification and Determination 

of the Effective Date 

Providing an opportunity for public 

comments prior to adopting these AD 

requirements would delay 

implementing the safety actions needed 

to correct this known unsafe condition. 

Therefore, we find that the risk to the 

flying public justifies waiving notice 

and comment prior to the adoption of 

this rule because the required corrective 

actions must be accomplished within 

two weeks. 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we determined that notice and 

opportunity for prior public comment 

before issuing this AD are impracticable 

and that good cause exists to make this 

AD effective in less than 30 days. 

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. 

We are 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 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national Government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed, I certify 

that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska to the extent that it justifies 

making a regulatory distinction; and 

4. 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2018–02–08 Bell Helicopter Textron: 

Amendment 39–19161; Docket No. 


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2360 Federal Register / Vol. 83, No. 11 / Wednesday, January 17, 2018 / Rules and Regulations 

FAA–2017–0895; Product Identifier 

2017–SW–048–AD. 

(a) Applicability 

This AD applies to Bell Helicopter Textron 

(Bell) Model 204B, 205A, and 205A–1 

helicopters with a Helicopter Technology 

Company (HTC) main rotor (M/R) blade part 

number 204P2100–101 installed, certificated 

in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in an M/R blade, which could result in 

failure of an M/R blade and subsequent loss 

of helicopter control. 

(c) Effective Date 

This AD becomes effective February 1, 

2018. 

(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) Within 25 hours time-in-service (TIS) or 

2 weeks, whichever occurs first, and 

thereafter at intervals not to exceed 25 hours 

TIS or 2 weeks, whichever occurs first, clean 

the upper and lower exposed surfaces of each 

M/R blade from an area starting at the butt 

end of the blade to three inches outboard of 

the doublers. Using a 3X or higher power 

magnifying glass and a light, inspect as 

follows: 

(i) Visually inspect the exposed areas of the 

lower grip pad and upper and lower grip 

plates of each M/R blade for a crack and any 

corrosion. 

(ii) On the upper and lower exposed 

surfaces of each M/R blade from blade 

stations 24.5 to 35 for the chord width, 

visually inspect each layered doubler and 

blade skin for a crack and any corrosion. Pay 

particular attention for any cracking in a 

doubler or skin near or at the same blade 

station as the blade retention bolt hole (blade 

station 28). 

(iii) Visually inspect the exposed areas of 

each bond line at the edges of the lower grip 

pad, upper and lower grip plates, and each 

layered doubler (bond lines) on the upper 

and lower surfaces of each M/R blade for the 

entire length and chord width for an edge 

void, any corrosion, loose or damaged 

adhesive squeeze-out, and an edge 

delamination. Pay particular attention to any 

crack in the paint finish that follows the 

outline of a grip pad, grip plate, or doubler, 

and to any loose or damaged adhesive 

squeeze-out, as these may be the indication 

of an edge void. 

(2) If there is a crack, any corrosion, an 

edge void, loose or damaged adhesive 

squeeze-out, or an edge delamination during 

any inspection in paragraph (e)(1) of this AD, 

before further flight, do the following: 

(i) If there is a crack in a grip pad or any 

grip plate or doubler, replace the M/R blade 

with an airworthy M/R blade. 

(ii) If there is a crack in the M/R blade skin 

that is within maximum repair damage 

limits, repair the M/R blade. If the crack 

exceeds maximum repair damage limits, 

replace the M/R blade with an airworthy M/ 

R blade. 

(iii) If there is any corrosion within 

maximum repair damage limits, repair the M/ 

R blade. If the corrosion exceeds maximum 

repair damage limits, replace the M/R blade 

with an airworthy M/R blade. 

(iv) If there is an edge void in the grip pad 

or in a grip plate or doubler, determine the 

length and depth using a feeler gauge. Repair 

the M/R blade if the edge void is within 

maximum repair damage limits or replace the 

M/R blade with an airworthy M/R blade. 

(v) If there is an edge void in a grip plate 

or doubler near the outboard tip, tap inspect 

the affected area to determine the size and 

shape of the void. Repair the M/R blade if the 

edge void is within maximum repair damage 

limits or replace the M/R blade with an 

airworthy M/R blade. 

(vi) If there is any loose or damaged 

adhesive squeeze-out along any of the bond 

lines, trim or scrape away the adhesive 

without damaging the adjacent surfaces or 

parent material of the M/R blade. Determine 

if there is an edge void or any corrosion by 

lightly sanding the trimmed area smooth 

using 280 or finer grit paper. If there is no 

edge void or corrosion, refinish the sanded 

area. 

(vii) If there is an edge delamination along 

any of the bond lines or a crack in the paint 

finish, determine if there is an edge void or 

a crack in the grip pad, grip plate, doubler, 

or skin by removing paint from the affected 

area by lightly sanding in a span-wise 

direction using 180–220 grit paper. If there 

are no edge voids and no cracks, refinish the 

sanded area. 

(viii) If any parent material is removed 

during any sanding or trimming in 

paragraphs (e)(2)(vi) or (e)(2)(vii) of this AD, 

repair the M/R blade if the damage is within 

maximum repair damage limits or replace the 

M/R blade with an airworthy M/R blade. 

(3) If there is a crack during any inspection 

in paragraph (e)(1) of this AD, within 10 days 

after completing the inspection, report the 

information requested in Appendix 1 to this 

AD by mail to the Los Angeles ACO Branch, 

Compliance and Airworthiness Division, 

FAA, 3960 Paramount Blvd., Lakewood, 

California 90712; attn. Galib Abumeri; or by 

email to galib.abumeri@faa.gov. 

(f) Special Flight Permits 

Special flight permits are prohibited. 

(g) 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 current 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 30 minutes 

per response, including the time for 

reviewing instructions, completing and 

reviewing the collection of information. All 

responses to this collection of information 

are mandatory. Comments concerning the 

accuracy of this burden and suggestions for 

reducing the burden should be directed to 

the FAA at: 800 Independence Ave. SW, 

Washington, DC 20591, Attn: Information 

Collection Clearance Officer, AES–200. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles ACO Branch, 

FAA, may approve AMOCs for this AD. Send 

your proposal to: Galib Abumeri, Aerospace 

Engineer (Structures), Airframe Section, Los 

Angeles ACO Branch, Compliance and 

Airworthiness Division, FAA, 3960 

Paramount Blvd., Lakewood, California 

90712; telephone 562–627–5324; email 

galib.abumeri@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest 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. 

(i) Additional Information 

HTC Service Notice No. 204–2100–1, dated 

July 5, 2017; Alert Service Bulletin (ASB) No. 

UH–1H–13–09, dated January 14, 2013; Bell 

ASB No. 204–75–1 and Bell ASB No. 205– 

75–5, both Revision C and both dated April 

25, 1979, which are not incorporated by 

reference, contain additional information 

about the subject of this AD. For service 

information identified in this AD, contact 

Bell Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, TX 76101; telephone (817) 280– 

3391; fax (817) 280–6466; or at http://

www.bellcustomer.com/files/. You may 

review this service information at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 10101 Hillwood Pkwy., Room 6N– 

321, Fort Worth, TX 76177. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6210, Main Rotor Blades. 

Issued in Fort Worth, Texas, on January 9, 

2018. 

James A. Grigg, 

Acting Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

Appendix 1 to AD 2018–02–08 

Please report the following information by 

mail to the Los Angeles ACO Branch, 

Compliance and Airworthiness Division, 

FAA, 3960 Paramount Blvd., Lakewood, 

California 90712; attn. Galib Abumeri; or by 

email to galib.abumeri@faa.gov. 

(1) Date of inspection: 

(2) Aircraft N-number: 

(3) M/R blade serial number: 

(4) M/R blade hours of time-in-service: 

(5) Location of each crack: 

(6) Dimension of each crack: 

(7) Primary operating location of the M/R 

blade: 

[FR Doc. 2018–00660 Filed 1–16–18; 8:45 am] 

BILLING CODE 4910–13–P 


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