Federal Register / Vol. 81, No. 87 / Thursday, May 5, 2016 / Proposed Rules 27055 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3821; Directorate 

Identifier 2014–SW–025–AD 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 75–26–05 

for Bell Helicopter Textron (Bell) Model 

204B, 205A–1 and 212 helicopters. AD 

75–26–05 currently requires removing 

and visually inspecting each main rotor 

(M/R) blade and, depending on the 

inspection’s outcome, repairing or 

replacing the M/R blades. This proposed 

AD would require more frequent 

inspections of certain M/R blades and 

would also apply to Model 205A 

helicopters. This proposed AD would 

have no requirement that helicopter 

blades be removed to conduct the initial 

visual inspections. These proposed 

actions are intended to detect a crack 

and prevent failure of an M/R blade and 

subsequent loss of helicopter control. 

DATES: We must receive comments on 

this proposed AD by July 5, 2016. 

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–2015– 

3821; or in person at the Docket 

Operations Office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this proposed AD, the 

economic evaluation, any comments 

received and other information. The 

street address for the Docket Operations 

Office (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 proposed 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 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: 

Charles Harrison, Project Manager, Fort 

Worth Aircraft Certification Office, 

FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone (817) 222– 

5140; email charles.c.harrison@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

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 might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, 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 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 proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

On December 3, 1975, we issued AD 

75–26–05, Amendment 39–2457 (40 FR 

57783, December 12, 1975) for Bell 

Model 204B, 205A–1, and 212 

helicopters. AD 75–26–05 requires, at 

intervals not to exceed 12 months 

installed time, visually inspecting the 

grip pad, grip plates, doublers, drag 

plates, and adjacent surfaces for voids, 

edge voids, corrosion, cracks, and 

adhesive squeeze-out along bond lines. 

AD 75–26–05 prohibits returning to 

service any blade with a crack or an 

adhesive void exceeding certain limits. 

For damage within certain limits, the 

M/R blade can be repaired, refinished, 

and reinstalled. 

AD 75–26–05 was prompted by an 

evaluation of a cracked M/R blade that 

concludes that initial cracking resulted 

from corrosion. These actions were 

intended to detect a crack and corrosion 

and prevent further corrosion in the 

M/R blade inboard portion. 

Actions Since AD 75–26–05 Was Issued 

Since we issued AD 75–26–05, Bell 

has evaluated an M/R blade installed on 

a Model UH–1H helicopter with 

multiple fatigue cracks around the blade 

retention bolt hole. The cracks resulted 

from a void between the lower grip plate 

and the grip pad. A ‘‘substantial’’ void 

also was found at the outboard doubler 

tip on the lower blade surface. Different 

part-numbered M/R blades of the same 

type may also be installed on Model 

204B, 205A, and 205A–1 helicopters. 

We have determined that more frequent 

inspections than those required by AD 

75–26–05 are necessary to detect 

cracking or certain damage. While AD 

75–26–05 requires removing the blades 

from the M/R hub, the inspections in 

this proposed AD would not. AD 75– 

26–05 applies to the Model 212 

helicopter, and this proposed AD would 

not because similar inspections on 

Model 212 blades addressing the unsafe 

condition are required by AD 2011–23– 

02 (76 FR 68301, November 4, 2011). 

We are including specific partnumbered blades in the applicability so 

that the proposed AD would no longer 

be required if a new blade is designed 

that is not subject to the unsafe 

condition. 

FAA’s Determination 

We are proposing 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 

Bell issued Alert Service Bulletin 

(ASB) No. UH–1H–13–09, dated January 

14, 2013, for the Model UH–1H 

helicopter (ASB UH–1H–13–09). ASB 

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 

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

visual inspection, daily and at every 150 


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27056 Federal Register / Vol. 81, No. 87 / Thursday, May 5, 2016 / Proposed Rules 

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. Similar 

inspections are contained in Bell ASB 

No. 204–75–1 (ASB 204–75–1) and No. 

205–75–5 (ASB 205–75–5), both 

Revision C and both dated April 25, 

1979, for Bell Model 204B and 205A–1 

helicopters, respectively. ASB 204–75–1 

and ASB 205–75–5 call for daily 

inspections and for inspections, rework, 

and refinishing every 1,000 hours TIS or 

12 months, whichever occurs first. 

Proposed AD Requirements 

This proposed AD would require 

within 25 hours 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 surfaces of 

each M/R blade from an area starting at 

the butt end of the blade to three inches 

outboard of the doublers. The proposed 

AD also would require visually 

inspecting various M/R parts for a crack 

or corrosion using a 3X or higher power 

magnifying glass and a light. 

If there is a crack, corrosion, an edge 

void, loose or damaged adhesive 

squeeze-out, or an edge delamination 

before further flight, this proposed AD 

would require repairing the M/R blade 

or replacing it with an airworthy M/R 

blade, depending on the condition’s 

severity. 

Differences Between This Proposed AD 

and the Service Information 

The proposed AD would require all 

inspections every 25 hours TIS or 2 

weeks, whichever occurs first. ASB UH– 

1H–13–09 specifies a one-time 

inspection within 10 hours TIS, and 

then a second repetitive inspection 

daily and at every 150 hours TIS, while 

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. This proposed 

AD contains more detailed inspection 

requirements and a more specific 

inspection area than the instructions in 

ASB UH–1H–13–09. The service 

information applies to M/R blade, part 

number (P/N) 204–011–250, and was 

issued for Model 204B and 205A–1 

helicopters. The proposed AD also 

applies to P/N 204–011–200, because 

this blade is of the same type and 

susceptible to the unsafe condition. The 

proposed AD also applies to certain 

M/R blades installed on the Model 205A 

helicopters. While none of these models 

are registered in the U.S., they were 

included because of blade P/N 

eligibility. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 52 helicopters of U.S. 

Registry and that labor costs average $85 

a 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) would require a half workhour. No parts would be needed. At an 

estimated 24 inspections a year, the cost 

would be $1,032 per helicopter and 

$53,664 for the U.S. fleet. 

Replacing an M/R blade would 

require 12 work hours and parts would 

cost $90,656 for a total cost of $91,676 

per blade. 

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

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 proposed 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. 

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 

removing Airworthiness Directive (AD) 

No. 75–26–05, Amendment 39–2457 (40 

FR 57783, December 12, 1975), and 

adding the following new AD: 

Bell Helicopter Textron: Docket No. FAA– 

2015–3821; Directorate Identifier 2014– 

SW–025–AD. 

(a) Applicability 

This AD applies to Model 204B, 205A, and 

205A–1 helicopters with a main rotor (M/R) 

blade, part number (P/N) 204–011–200–001 

or P/N 204–011–250–(all dash numbers), 

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) Affected ADs 

This AD supersedes AD 75–26–05, 

Amendment 39–2457 (40 FR 57783, 

December 12, 1975). 

(d) Comments Due Date 

We must receive comments by July 5, 2016. 

(e) 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. 

(f) 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: 


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Federal Register / Vol. 81, No. 87 / Thursday, May 5, 2016 / Proposed Rules 27057 

(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 (f)(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 (f)(2)(vi) or (f)(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. 

(g) Special Flight Permit 

Special flight permits are prohibited. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Fort Worth Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

Charles Harrison, Project Manager, Fort 

Worth Aircraft Certification Office, FAA, 

10101 Hillwood Pkwy, Fort Worth, TX 

76177; telephone (817) 222–5140; email 7- 

AVS-ASW-170@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 

Bell Helicopter Alert Service Bulletin 

(ASB) No. UH–1H–13–09, dated January 14, 

2013, and ASB No. 204–75–1 and 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 the 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 April 15, 

2016. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–10523 Filed 5–4–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3941; Directorate 

Identifier 2015–SW–052–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for Airbus 

Helicopters Deutschland GmbH (Airbus 

Helicopters) Model MBB–BK 117A–3, 

MBB–BK 117A–4, MBB–BK 117B–1, 

MBB–BK 117B–2, and MBB–BK 117C– 

1 helicopters. This proposed AD would 

require removing adhesive seals from 

the exterior and interior door jettisoning 

system on the left and right sliding 

doors. This proposed AD is prompted 

by reports that the adhesive seal 

prevented the doors from jettisoning 

properly. The proposed actions are 

intended to remove the adhesive seal to 

allow the doors to jettison properly so 

occupants can exit the helicopter during 

an emergency. 

DATES: We must receive comments on 

this proposed AD by July 5, 2016. 

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–2015– 

3941; or in person at the Docket 

Operations Office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this proposed AD, the 

European Aviation Safety Agency 

(EASA) AD, the economic evaluation, 


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