83660 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations 

ST00830SE is installed, a ‘‘change in 

product’’ alternative method of compliance 

(AMOC) approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder (DAH) indicating 

that the stringer (S)–14L and S–14R lap 

splices are subject to widespread fatigue 

damage (WFD). We are issuing this AD to 

detect and correct widespread cracking in the 

S–14L and S–14R lap splices that could 

rapidly link up and result in possible rapid 

decompression and reduced structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

At the applicable compliance time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1352, 

Revision 1, dated March 10, 2016, do a low 

frequency eddy current inspection for 

cracking of the lower fastener row of S–14L 

and S–14R lap splices, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–53A1352, 

Revision 1, dated March 10, 2016. Repeat the 

inspection thereafter at the applicable times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1352, 

Revision 1, dated March 10, 2016. If any 

cracking is found, before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (i) of 

this AD. 

(h) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 737–53A1352, dated October 

2, 2015. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (j) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (i)(4)(i) and (i)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. An AMOC is required for any 

deviations to RC steps, including substeps 

and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(j) Related Information 

For more information about this AD, 

contact Gaetano Settineri, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle ACO, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6577; fax: 425–917–6590; email: 

gaetano.settineri@faa.gov. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 737– 

53A1352, Revision 1, dated March 10, 2016. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110–SK57, Seal Beach, CA 90740; 

telephone 562–797–1717; Internet https://

www.myboeingfleet.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

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

Issued in Renton, Washington, on October 

21, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–26621 Filed 11–21–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3820; Directorate 

Identifier 2014–SW–024–AD; Amendment 

39–18716; AD 2016–23–09] 

RIN 2120–AA64 

Airworthiness Directives; Various 

Restricted Category Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for various 

restricted category helicopters. This AD 

requires cleaning and visually 

inspecting certain main rotor (M/R) 

blades and, depending on the outcome 

of the inspections, repairing or replacing 

the M/R blades. This AD was prompted 

by a report of an M/R blade with 

multiple fatigue cracks around the blade 

retention bolt hole. The actions are 

intended to detect a crack in the M/R 

blade, and prevent failure of the M/R 

blade and subsequent loss of helicopter 

control. 

DATES: This AD is effective December 

27, 2016. 

ADDRESSES: 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 a copy of the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy, Room 6N–321, Fort Worth, TX 

76177. 

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– 

3820; 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 AD, the economic 

evaluation, any comments received, and 

other information. The street address for 


sradovich on DSK3GMQ082PROD with RULES
Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations 83661 

the Docket Operations Office (phone: 

800–647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Charles Harrison, Project Manager, Fort 

Worth Aircraft Certification Office, 

10101 Hillwood Pkwy., Fort Worth, 

Texas 76177; telephone 817–222–5140; 

email Charles.C.Harrison@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On April 11, 2016, at 81 FR 21288, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 by 

adding an AD that would apply to 

Model TH–1F, UH–1B, UH–1F, UH–1H, 

and UH–1P helicopters with a M/R 

blade, part number 204–011–250–005 or 

204–011–250–113, installed. The NPRM 

proposed to require repetitively 

cleaning and visually inspecting the M/ 

R blades for a crack, corrosion, an edge 

void, loose or damaged adhesion, and 

an edge delamination. Depending on the 

outcome of the inspections, the NPRM 

proposed repairing or replacing the M/ 

R blades. The actions in the NPRM were 

prompted by a Bell Helicopter Textron 

Inc. evaluation of an M/R blade 

installed on a Model UH–1H helicopter 

that had 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. A different part-numbered M/R 

blade of the same type installed on the 

Model UH–1H helicopter may also be 

installed on Model TH–1F, UH–1B, UH– 

1F, and UH–1P helicopters. 

These actions are intended to detect a 

crack in an M/R blade, and prevent 

failure of the M/R blade, and subsequent 

loss of helicopter control. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(81 FR 21288, April 11, 2016). 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

Related Service Information 

Bell Helicopter issued 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 time-inservice (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. 

Bell Helicopter Textron also issued 

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 call for visually inspecting the 

M/R blades during each daily inspection 

and repetitively washing the blades and 

applying WD–40. 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, or within 150 

hours or 30 days, whichever occurs first, 

if the blades have more 1,000 hours of 

operation or have been in service more 

than 12 months. While ASB No. 204– 

75–1 and ASB No. 205–75–5 do not 

apply to the helicopters that are the 

subject of this AD, they do apply to the 

affected M/R blades. 

Differences Between This AD and the 

Service Information 

ASB No. UH–1H–13–09 specifies a 

one-time inspection and then a second 

repetitive inspection daily and at every 

150 hours TIS, and ASB No. 204–75–1 

and ASB 205–75–5 call for visually 

inspecting the M/R blades daily and 

every 1,000 hours TIS or 12 months, 

whichever occurs first. This AD requires 

all inspections at intervals not to exceed 

25 hours TIS or two weeks, whichever 

occurs first. This AD contains more 

detailed inspection requirements and a 

more specific inspection area than the 

instructions in ASB No. UH–1H–13–09. 

Lastly, ASB No. UH–1H–13–09 applies 

to Model UH–1H helicopters with M/R 

blade P/N 204–011–250–113, ASB No. 

204–75–1 applies to Model 204B 

helicopters with M/R blade P/N 204– 

011–250 (all dash numbers), and ASB 

No. 205–75–5 applies to Model 205A– 

1 helicopters with M/R blade P/N 204– 

011–250 (all dash numbers). This AD 

applies to Model TH–1F, UH–1B, UH– 

1F, UH–1H, and UH–1P helicopters 

with M/R blade P/N 204–011–250–005 

or 204–011–250–113. 

Costs of Compliance 

We estimate that this AD affects 607 

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) requires a total of 1⁄2 workhour. No parts are needed. At an 

estimated 24 inspections a year, the cost 

would be $1,032 per helicopter and 

$626,424 for the U.S. fleet. 

• Replacing an M/R blade requires 12 

work hours while parts 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 

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 above, 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 


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83662 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations 

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): 

2016–23–09 Various Restricted Category 

Helicopters: Amendment 39–18716; 

Docket No. FAA–2015–3820; Directorate 

Identifier 2014–SW–024–AD. 

(a) Applicability 

This AD applies to Model TH–1F, UH–1B, 

UH–1F, UH–1H, and UH–1P helicopters with 

a main rotor (M/R) blade, part number 204– 

011–250–005 or 204–011–250–113, installed. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

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

failure of the M/R blade and subsequent loss 

of helicopter control. 

(c) Effective Date 

This AD becomes effective December 27, 

2016. 

(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 area 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 entire 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. 

(f) Special Flight Permits 

Special flight permits are prohibited. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: Charles Harrison, 

Project Manager, Fort Worth Aircraft 

Certification Office, 10101 Hillwood Pkwy., 

Fort Worth, Texas 76177; telephone 817– 

222–5140; email 9-ASW-FTW-AMOCRequests@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. 

(h) Additional Information 

Bell Helicopter Alert Service Bulletin 

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

2013, and Bell Helicopter Textron ASB No. 

204–75–1 and ASB 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 final rule. 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 a copy of this service information at 

the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6210, Main Rotor Blades. 

Issued in Fort Worth, Texas, on November 

4, 2016. 

Lance T. Gant, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2016–27767 Filed 11–21–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–4223; Directorate 

Identifier 2015–NM–108–AD; Amendment 

39–18693; AD 2016–22–04] 

RIN 2120–AA64 

Airworthiness Directives; Gulfstream 

Aerospace Corporation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 


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