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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Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations 83663 

Gulfstream Aerospace Corporation 

Model GV and GV–SP airplanes. This 

AD was prompted by a new revision to 

the Airworthiness Limitations Section 

(ALS) of the Aircraft Maintenance 

Manual (AMM) based on fatigue and 

damage tolerance testing, and updated 

analysis. This AD requires revising the 

maintenance or inspection program to 

incorporate updated inspection 

requirements and life limits that address 

fatigue cracking of principal structural 

elements (PSEs). We are issuing this AD 

to ensure that fatigue cracking of PSEs 

is detected and corrected; such fatigue 

cracking could result in reduced 

structural integrity of the PSEs and 

critical components. 

DATES: This AD is effective December 

27, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 27, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Gulfstream Aerospace Corporation, 

Technical Publications Dept., P.O. Box 

2206, Savannah, GA 31402–2206; 

telephone: 800–810–4853; fax: 912– 

965–3520; email: pubs@gulfstream.com; 

Internet: http://www.gulfstream.com/ 

product_support/technical_pubs/pubs/ 

index.htm. You may view this 

referenced 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. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2016–4223. 

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–2016– 

4223; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Ronald Wissing, Aerospace Engineer, 

Airframe Branch, ACE–117A, FAA, 

Atlanta Aircraft Certification Office 

(ACO), 1701 Columbia Avenue, College 

Park, GA 30337; phone: 404–474–5552; 

fax: 404–474–5606; email: 

ronald.wissing@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Gulfstream Aerospace 

Corporation Model GV and GV–SP 

airplanes. The NPRM published in the 

Federal Register on March 14, 2016 (81 

FR 13301) (‘‘the NPRM’’). The NPRM 

was prompted by a new revision to the 

ALS of the AMM, Chapter 05–10–10, 

based on fatigue and damage tolerance 

testing, and updated analysis. The 

NPRM proposed to require revising the 

maintenance or inspection program to 

update inspection requirements and life 

limits that address fatigue cracking of 

principal structural elements (PSEs). We 

are issuing this AD to ensure that fatigue 

cracking of PSEs is detected and 

corrected; such fatigue cracking could 

result in reduced structural integrity of 

the PSEs and critical components. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Specify Referenced 

Document 

Gulfstream requested that we revise 

the SUMMARY section and the Discussion 

section of the NPRM, and paragraph (e) 

of the proposed AD, to refer to the 

AMM, Chapter 05–10–10, which 

contains updated inspection 

requirements and life limits. 

We agree with the request. We have 

revised the SUMMARY and Discussion 

sections of this final rule, and paragraph 

(e) of this AD accordingly. 

Request To Remove Certain Language 

From the NPRM 

Gulfstream requested that we revise 

the FAA’s Determination section of the 

NPRM, which states that the unsafe 

condition is likely to exist or develop 

‘‘in other products of the same type 

design.’’ Gulfstream requested that we 

remove the quoted language, and 

pointed out that they believe the 

statement is irrelevant to the unsafe 

condition. 

We disagree with the commenter’s 

request. Our phrasing is intentional. The 

finding that the condition is likely to 

exist or develop in other products of the 

same type design is necessary to ensure 

that the AD falls within the scope of 14 

CFR part 39 (‘‘Airworthiness 

Directives’’.) (Specifically, see 14 CFR 

39.5.) Additionally, the FAA’s 

Determination section of the NPRM is 

not restated in this final rule. We have 

not changed this AD regarding this 

issue. 

Request for Clarification of Certain 

Language From the NPRM 

Gulfstream requested clarification 

regarding which ‘‘operator maintenance 

documents’’ require revision. 

Gulfstream did not provide any 

justification for its request. 

We agree that clarification is 

necessary. Regardless of the 

maintenance program that an operator 

uses, this AD requires revising the 

applicable maintenance or inspection 

program documentation. The owner or 

operator is responsible for maintaining 

its fleet in an airworthy condition, 

including compliance with 14 CFR part 

39. This final rule has not been changed 

in this regard. 

Request To Clarify Applicability 

Gulfstream requested that we revise 

the ‘‘Differences Between This Proposed 

AD and the Service Information’’ 

section of the NPRM. Gulfstream 

pointed out that they believe the 

applicability is contradictory to 

Gulfstream Document GV–GER–9973, 

Summary of Changes to the GV Series 

Airworthiness Limitations, Revision C, 

dated January 8, 2015. Gulfstream also 

mentioned that it does not believe an 

operator would be able to log 

compliance with the proposed AD. 

We agree to clarify. The applicability 

of this AD differs from the effectivity of 

Gulfstream Document GV–GER–9973, 

Summary of Changes to the GV Series 

Airworthiness Limitations, Revision C, 

dated January 8, 2015, which excludes 

airplanes on which certain 

supplemental type certificates (STCs) 

have been accomplished. Airplanes on 

which those STCs have been 

accomplished are included in the 

applicability of this AD because those 

airplanes could have inspections and 

limits that are applicable. If it is 

determined that an airplane with a 

listed STC cannot accomplish the 

requirements of this AD, the operator 

may request an alternative method of 

compliance (AMOC) in accordance with 

paragraph (i) of this AD. 

Also, we do not agree with the 

statement in Gulfstream Document GV– 

GER–9973, Summary of Changes to the 

GV Series Airworthiness Limitations, 

Revision C, dated January 8, 2015, 

indicating that airplanes with specific 

STCs installed should be excluded from 

the effectivity of Gulfstream Document 

GV–GER–9973, Summary of Changes to 


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83664 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations 

the GV Series Airworthiness 

Limitations, Revision C, dated January 

8, 2015. We have not changed this AD 

in this regard. 

Request To Allow the Use of LaterApproved Service Information 

Gulfstream requested that we revise 

Note 1 to paragraph (g) of the proposed 

AD. Gulfstream specifically requested 

adding language that would specify ‘‘or 

later FAA approved revision’’ to clarify 

operator compliance with the proposed 

AD. 

We do not agree to revise Note 1 to 

paragraph (g) of this AD to allow use of 

‘‘later FAA-approved revisions.’’ Note 1 

to paragraph (g) of this AD specifies the 

AMM revisions specifically identified in 

Gulfstream Document GV–GER–9973, 

Summary of Changes to the GV Series 

Airworthiness Limitations, Revision C, 

dated January 8, 2015. This AD does not 

require any actions to be done in 

accordance with the AMM revisions 

specified in Note 1 to paragraph (g) of 

this AD. Additionally, we may not refer 

to any document that does not yet exist. 

However, we have revised Note 1 to 

paragraph (g) of this AD to clarify the 

intent of that note. 

Request To Verify the Contact 

Information for Gulfstream 

Gulfstream requested that we verify 

the contact information used in the 

ADDRESSES section and paragraph (k)(3) 

of this AD before publication. 

Gulfstream stated that its contact 

information and data storage location 

may change before the publication date 

of the final rule. 

We have verified the contact 

information used in the ADDRESSES

section of this final rule, and found that 

no change is necessary. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR part 51 

We reviewed Gulfstream Document 

GV–GER–9973, Summary of Changes to 

the GV Series Airworthiness 

Limitations, Revision C, dated January 

8, 2015. The service information 

describes inspection requirements and 

life limits that address fatigue cracking 

of the PSEs. 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. 

Costs of Compliance 

We estimate that this AD affects 392 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Revision of the maintenance or inspection 

program.

1 work-hour × $85 per hour = $85 ................. $0 $85 $33,320 

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, 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. 

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): 

2016–22–04 Gulfstream Aerospace 

Corporation: Amendment 39–18693; 

Docket No. FAA–2016–4223; Directorate 

Identifier 2015–NM–108–AD. 

(a) Effective Date 

This AD is effective December 27, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Gulfstream Aerospace 

Corporation Model GV airplanes, certificated 

in any category, serial numbers 501 through 

693 inclusive and serial number 699; and 

Model GV–SP airplanes, certificated in any 

category, serial numbers 5001 through 5433 

inclusive. 


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Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations 83665 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear; 53, 

Fuselage; 54, Nacelles/Pylons; 55, Stabilizers; 

and 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a new revision 

to the Airworthiness Limitations Section 

(ALS) of the Aircraft Maintenance Manual 

(AMM), Chapter 05–10–10, based on fatigue 

and damage tolerance testing, and updated 

analysis. We are issuing this AD to ensure 

fatigue cracking of principal structural 

elements (PSEs) is detected and corrected; 

such fatigue cracking could result in reduced 

structural integrity of the PSEs and critical 

components. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revise Maintenance or Inspection 

Program 

Within 12 months after the effective date 

of this AD, revise the maintenance or 

inspection program, as applicable, to 

incorporate the airworthiness limitations 

specified in Gulfstream Document GV–GER– 

9973, Summary of Changes to the GV Series 

Airworthiness Limitations, Revision C, dated 

January 8, 2015. The initial compliance times 

for the tasks identified in Gulfstream 

Document GV–GER–9973, Summary of 

Changes to the GV Series Airworthiness 

Limitations, Revision C, dated January 8, 

2015, are at the applicable times specified in 

Gulfstream Document GV–GER–9973, 

Summary of Changes to the GV Series 

Airworthiness Limitations, Revision C, dated 

January 8, 2015, or within twelve months 

after the effective date of this AD, whichever 

occurs later. 

Note 1 to paragraph (g) of this AD: 

Gulfstream Document GV–GER–9973, 

Summary of Changes to the GV Series 

Airworthiness Limitations, Revision C, dated 

January 8, 2015, specifies the following AMM 

revisions as additional sources of guidance 

for the actions required by paragraph (g) of 

this AD. For Model GV airplanes, AMM 

Revision 43, dated February 15, 2015; and for 

Model GV–SP airplanes, G500 or G550 AMM 

Revision 24, dated February 15, 2015, as 

applicable. 

(h) No Alternative Actions or Intervals 

After the maintenance or inspection 

program has been revised as required by 

paragraph (g) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (i) of this 

AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta 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. 

(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. 

(j) Related Information 

For more information about this AD, 

contact Ronald Wissing, Aerospace Engineer, 

Airframe Branch, ACE–117A, FAA, Atlanta 

ACO, 1701 Columbia Avenue, College Park, 

GA 30337; phone: 404–474–5552; fax: 404– 

474–5606; email: ronald.wissing@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) Gulfstream Document GV–GER–9973, 

Summary of Changes to the GV Series 

Airworthiness Limitations, Revision C, dated 

January 8, 2015. The revision level and date 

of this document are not specified on the title 

page of the document. 

(ii) Reserved. 

(3) For Gulfstream Aerospace Corporation 

service information identified in this AD, 

contact Gulfstream Aerospace Corporation, 

Technical Publications Dept., P.O. Box 2206, 

Savannah, GA 31402–2206; telephone: 800– 

810–4853; fax: 912–965–3520; email: pubs@

gulfstream.com; Internet: http://

www.gulfstream.com/product_support/ 

technical_pubs/pubs/index.htm. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA 98057–3356. 

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 

14, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–25743 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–2016–6672; Directorate 

Identifier 2016–NM–022–AD; Amendment 

39–18706; AD 2016–22–17] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 787–8 

airplanes. This AD was prompted by a 

report that the grounding jumpers 

between the environmental control 

system (ECS) bracket and the current 

return network (CRN) straps near certain 

passenger entry doors were not bonded 

correctly during manufacturing. This 

AD requires changing the configuration 

of the grounding jumpers connecting the 

ECS brackets and CRN straps; measuring 

the bond resistance; and doing related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective December 

27, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 27, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Data & Services Management, 

P. O. Box 3707, MC 2H–65, Seattle, WA 

98124–2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; Internet 

https://www.myboeingfleet.com. You 

may view this referenced 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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

6672. 

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–2016– 

6672; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 


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