95854 Federal Register / Vol. 81, No. 250 / Thursday, December 29, 2016 / Rules and Regulations 

or by the private sector, of $100 million 

or more (as adjusted for inflation) in any 

one year. 

Congressional Review Act 

The final rule is not a major rule as 

defined in 5 U.S.C. chapter 8, 

Congressional Review of Agency 

Rulemaking. 

Executive Orders 12866 and 13563 

In promulgating this final rule, the 

Office of Government Ethics has 

adhered to the regulatory philosophy 

and the applicable principles of 

regulation set forth in Executive Orders 

12866 and 13563. This rule has not been 

reviewed by the Office of Management 

and Budget under Executive Order 

12866 because it is not a ‘‘significant’’ 

regulatory action for the purposes of 

that order. 

Executive Order 12988 

As Director of the Office of 

Government Ethics, I have reviewed this 

final rule in light of section 3 of 

Executive Order 12988, Civil Justice 

Reform, and certify that it meets the 

applicable standards provided therein. 

List of Subjects in 5 CFR Part 2641 

Conflict of interests, Government 

employees. 

Approved: December 22, 2016. 

Walter M. Shaub, Jr., 

Director,Office of Government Ethics. 

Accordingly, for the reasons set forth 

in the preamble, the Office of 

Government Ethics is amending 5 CFR 

part 2641 as set forth below: 

PART 2641—POST-EMPLOYMENT 

CONFLICT OF INTEREST 

RESTRICTIONS 

■ 1. The authority citation for part 2641 

continues to read as follows: 

Authority: 5 U.S.C. app. (Ethics in 

Government Act of 1978); 18 U.S.C. 207; E.O. 

12674, 54 FR 15159, 3 CFR, 1989 Comp., p. 

215, as modified by E.O. 12731, 55 FR 42547, 

3 CFR, 1990 Comp., p. 306. 

■ 2. Amend appendix B to part 2641 as 

follows: 

■ a. Revise the listings for Parent: 

Department of Labor and Parent: 

Department of Transportation. 

■ b. Effective March 29, 2017, remove 

the Employment Standards 

Administration component from the 

listing for Parent: Department of Labor 

■ c. Effective March 29, 2017, remove 

the Surface Transportation Board 

component from the listing for Parent: 

Department of Transportation. 

The revisions read as follows: 

Appendix B to Part 2641—Agency 

Components for Purposes of 18 U.S.C. 

207(c) 

* * * * * 

Parent: Department of Labor 

Components: 

Bureau of Labor Statistics. 

Employee Benefits Security Administration 

(formerly Pension and Welfare Benefits 

Administration) (effective May 16, 1997). 

Employment and Training Administration. 

Employment Standards Administration. 

Mine Safety and Health Administration. 

Occupational Safety and Health 

Administration. 

Office of Disability Employment Policy 

(effective January 30, 2003). 

Office of Federal Contract Compliance 

Programs (effective December 29, 2016). 

Office of Labor Management Standards 

(effective December 29, 2016). 

Office of Workers’ Compensation Programs 

(effective December 29, 2016). 

Pension Benefit Guaranty Corporation 

(effective May 25, 2011). 

Wage and Hour Division (effective December 

29, 2016). 

* * * * * 

Parent: Department of Transportation 

Components: 

Federal Aviation Administration. 

Federal Highway Administration. 

Federal Motor Carrier Safety Administration 

(effective January 30, 2003). 

Federal Railroad Administration. 

Federal Transit Administration. 

Maritime Administration. 

National Highway Traffic Safety 

Administration. 

Pipeline and Hazardous Materials Safety 

Administration (effective December 29, 

2016). 

Saint Lawrence Seaway Development 

Corporation. 

Surface Transportation Board (effective May 

16, 1997). 

* * * * * 

[FR Doc. 2016–31457 Filed 12–28–16; 8:45 am] 

BILLING CODE 6345–03–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0498; Directorate 

Identifier 2013–SW–052–AD; Amendment 

39–18745; AD 2016–25–19] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Previously Eurocopter 

France) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2010–21– 

07 for Eurocopter France (now Airbus 

Helicopters) Model AS350B3 and 

EC130B4 helicopters. AD 2010–21–07 

required inspecting the pilot’s and copilot’s throttle twist for proper operation 

of the contactors. This new AD retains 

the requirements of AD 2010–21–07, 

includes additional inspection 

procedures, and revises the inspection 

interval. These actions are intended to 

address the unsafe condition on these 

products. 

DATES: This AD is effective February 2, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 2, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, Inc., 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may view this referenced service 

information at the FAA, Office of the 

Regional Counsel, 10101 Hillwood 

Parkway, Fort Worth, Texas, 76177. It is 

also available on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0498. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov in Docket No. 

FAA–2014–0498; 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 European 

Aviation Safety Agency (EASA) AD, any 

incorporated-by-reference information, 

the economic evaluation, any comments 

received, and other information. The 

address for the Docket Office (phone: 

800–647–5527) is Document 

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: 

George Schwab, Aviation Safety 

Engineer, Safety Management Group, 

Rotorcraft Directorate, FAA, 10101 

Hillwood Parkway, Fort Worth, Texas, 

76101; telephone (817) 222–5110; email 

george.schwab@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to remove AD 2010–21–07, 

Amendment 39–16467 (75 FR 63052, 


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Federal Register / Vol. 81, No. 250 / Thursday, December 29, 2016 / Rules and Regulations 95855 

October 14, 2010) and add a new AD. 

AD 2010–21–07 required repetitively 

inspecting the pilot’s and co-pilot’s 

throttle twist for proper operation of the 

contactors, which provide for changes 

between the ‘‘IDLE’’ and ‘‘FLIGHT’’ 

positions of the throttle twist grip 

control. The NPRM published in the 

Federal Register on July 30, 2014 (79 FR 

44142), and proposed to retain the 

inspection requirements of AD 2010– 

21–07 and included additional 

requirements to inspect for proper 

operation of contactors 53Ka and 53Kb 

and the pilot and copilot throttle twist 

grip controls for proper functioning. The 

NPRM also proposed to reduce the 

intervals of the inspections from 600 

hours time-in-service (TIS) to 300 hours 

TIS. 

The NPRM was prompted by AD No. 

2013–0191–E, dated August 22, 2013, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union. EASA advises that the 

switches in the engine ‘‘IDLE’’ or 

‘‘FLIGHT’’ control system could be 

affected by the corrosive effects of a saltladen atmosphere, which could lead to 

engine power loss. EASA states that 

these corrosive effects are not prevented 

by MOD 074263, which Eurocopter 

designed to address the unsafe 

condition identified in AD 2010–21–07. 

According to EASA, a subsequent 

accident occurred which involved 

power loss in flight of a Model AS350B3 

helicopter with MOD 074263 installed. 

As a result, EASA AD No. 2013–0191– 

E does not accept MOD 074263 as 

terminating action for the required 

repetitive maintenance actions. 

Accordingly, the two letters we issued 

approving MOD 074263 as an Alternate 

Method of Compliance for AD 2010–21– 

07 are no longer valid. 

Comments 

After our NPRM (79 FR 44142, July 

30, 2014) was published, we received 

comments from three commenters. 

Request 

Two commenters requested that we 

change the compliance times for the 

recurring inspection to allow for a 

longer compliance time for helicopters 

that do not operate in corrosive or salt 

laden environments. One commenter 

noted that the failures have been 

attributed to operations in a corrosive 

environment. The other commenter 

stated the proposed AD would penalize 

operators in non-salt laden 

environments by requiring the shorter 

compliance time. The commenters also 

requested that we adopt the same 

compliance intervals, 330 hours TIS or 

660 hours TIS for helicopters that do not 

operate in salt laden environments, 

allowed by the manufacturer’s service 

information. The commenters stated 

that this would facilitate maintenance 

scheduling. 

We agree. We are adding a longer 

recurring inspection compliance 

interval for helicopters that do not 

operate in salt laden conditions to 

match the manufacturer’s service 

information. We have also increased the 

compliance intervals for the recurring 

inspection to 330 hours TIS for 

helicopters operating in salt-laden 

environments and to 660 hours TIS for 

all other helicopters. 

One commenter requested that the 

proposed AD condition compliance 

with paragraph 3.B.2 of the 

manufacturer’s service information on 

the results of the inspection in 

paragraph 3.B.1. The commenter noted 

that the proposed AD requires 

compliance with paragraph 3.B.1 

through 3.B.6 of the service information, 

but does not clarify that compliance 

with paragraph 3.B.2 is only required if 

the aircraft fails the prior inspection. 

We agree that compliance with 

paragraph 3.B.2 of the service 

information is conditional, but we do 

not agree that a change to the AD 

language is necessary. There is no 

ambiguity in the service information 

incorporated by reference in the AD as 

to when compliance with paragraph 

3.B.2 is necessary. 

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 helicopters of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed, except for the changes 

described previously. We have also 

changed the service information that is 

incorporated by reference to the most 

current revision. These changes are 

consistent with the intent of the 

proposals in the NPRM (79 FR 44142, 

July 30, 2014) and will not increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Interim Action 

We consider this AD interim action. 

The design approval holder is currently 

developing a modification that will 

address the unsafe condition identified 

in this proposed AD. Once this 

modification is developed, approved, 

and available, we might consider 

additional rulemaking. 

Related Service Information Under 1 

CFR Part 51 

Since we published the NPRM (79 FR 

44142, July 30, 2014), Airbus 

Helicopters (previously Eurocopter) 

revised its service information. We 

reviewed one document that copublishes 3 Emergency Alert Service 

Bulletin (EASB) identification numbers: 

No. 05.00.61, Revision 3, dated June 15, 

2015, for Model AS350B3 helicopters; 

No. 05.00.41, Revision 2, dated June 15, 

2015, for the non-FAA type-certificated 

Model AS550C3 helicopter; and No. 

05A009, Revision 3, dated June 15, 

2015, for Model EC130B4 helicopters. 

EASB Nos. 05.00.61 and 05A009 are 

incorporated by reference in this AD. 

EASB No. 05.00.41 is not incorporated 

by reference in this AD. 

This service information describes 

procedures for a functional check and 

installation of a protection for microcontacts (microswitches) 53Ka, 53Kb, 

and 65K (IDLE/FLIGHT mode). EASA 

classified the prior revision of this 

service information as mandatory and 

issued EASA Emergency AD No. 2013– 

0191–E, dated August 22, 2013, to 

ensure the continued airworthiness of 

these helicopters. 

Because this revision of EASB No. 

05.00.61 and No. 05A009 specifies the 

same actions but clarifies the 

procedures used in applying varnish to 

the microswitches, we are incorporating 

this revision by reference in this AD. 

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 will affect 

517 helicopters of U.S. Registry. 

We estimate that operators will incur 

the following costs in order to comply 

with this AD. The average labor rate is 

$85 per work hour. It will take about 4 

work hours for the inspections and any 

necessary maintenance, for a total cost 

of $340 per helicopter and $175,780 for 

the U.S. fleet per inspection cycle. 

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 


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95856 Federal Register / Vol. 81, No. 250 / Thursday, December 29, 2016 / Rules and Regulations 

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 have 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 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 a regulatory 

distinction is required, 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 

removing Airworthiness Directive (AD) 

2010–21–07, Amendment 39–16467 (75 

FR 63052, October 14, 2010), and 

adding the following new AD: 

2016–25–19 Airbus Helicopters (Previously 

Eurocopter France) Helicopters: 

Amendment 39–18745; Docket No. 

FAA–2014–0498; Directorate Identifier 

2013–SW–052–AD. 

(a) Applicability 

This AD applies to Model AS350B3 and 

EC130B4 helicopters, certificated in any 

category, with the ARRIEL 2B1 engine with 

the two-channel Full Authority Digital 

Engine Control (FADEC) and with new twist 

grip modification (MOD) 073254 for the 

Model AS350B3 helicopter or MOD 073773 

for the Model EC130B4 helicopter, installed. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

failure of one of the two contactors, 53Ka or 

53Kb, which can prevent switching from 

‘‘IDLE’’ mode to ‘‘FLIGHT’’ mode during 

autorotation training making it impossible to 

recover from the practice autorotation and 

compelling the pilot to continue the 

autorotation to the ground. This condition 

could result in unintended touchdown to the 

ground at a flight-idle power setting during 

a practice autorotation, damage to the 

helicopter, and injury to occupants. 

(c) Affected ADs 

This AD supersedes AD 2010–21–07, 

Amendment 39–16467 (75 FR 63052, October 

14, 2010). 

(d) Effective Date 

This AD becomes effective February 2, 

2017. 

(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) Before the next practice autorotation or 

on or before 100 hours time-in-service (TIS), 

whichever occurs first, inspect the wiring, 

perform an insulation test, inspect the pilot 

and copilot throttle twist grip controls, and 

test the pilot and copilot throttle twist grip 

controls for proper functioning by following 

the Accomplishment Instructions, paragraph 

3.B.1 through 3.B.6, of Airbus Helicopters 

Emergency Alert Service Bulletin (EASB) No. 

05.00.61, Revision 3, dated June 15, 2015, for 

Model AS350B3 helicopters or EASB No. 

05A009, Revision 3, dated June 15, 2015, for 

Model EC130B4 helicopters, as appropriate 

for your model helicopter. 

(2) Repeat the inspections in paragraph 

(f)(1) of this AD at intervals not to exceed the 

following compliance times. For purposes of 

this AD, salt laden conditions exist when a 

helicopter performs a flight from a takeoff 

and landing area, heliport, or airport less 

than 0.5 statute mile from salt water or 

performs a flight within 0.5 statute mile from 

salt water below an altitude of 1,000 ft. above 

ground or sea level. 

(i) For helicopters that have operated in 

salt laden conditions since the previous 

inspection required by this AD, at intervals 

not to exceed 330 hours TIS. 

(ii) For helicopters that have not operated 

in salt laden conditions since the previous 

inspection required by this AD, at intervals 

not to exceed 660 hours TIS. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: George Schwab, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, 10101 

Hillwood Parkway, Fort Worth, Texas 76177; 

telephone (817) 222–5110; email 

george.schwab@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 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) 

Emergency AD No. 2013–0191–E, dated 

August 22, 2013. You may view the EASA 

AD at http://www.regulations.gov in Docket 

No. FAA–2014–0498. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 76 Engine Controls. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) Airbus Helicopters Emergency Alert 

Service Bulletin (EASB) No. 05.00.61, 

Revision 3, dated June 15, 2015. 

(ii) Airbus Helicopters EASB No. 05A009, 

Revision 3, dated June 15, 2015. 

Note 1 to paragraph (j)(2): Airbus 

Helicopters EASB No. 05.00.61, Revision 3, 

dated June 15, 2015, and Airbus Helicopters 

EASB No. 05A009, Revision 3, dated June 15, 

2015 are co-published as one document along 

with Airbus Helicopters EASB No. 05.00.41, 

Revision 2, dated June 15, 2015, which is not 

incorporated by reference in this AD. 

(3) For Airbus Helicopters service 

information identified in this final rule, 

contact Airbus Helicopters, Inc., 2701 N. 

Forum Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232–0323; 

fax (972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy, 

Room 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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. 


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Federal Register / Vol. 81, No. 250 / Thursday, December 29, 2016 / Rules and Regulations 95857 

Issued in Fort Worth, Texas, on December 

6, 2016. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–30020 Filed 12–28–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–6898; Directorate 

Identifier 2016–NM–010–AD; Amendment 

39–18752; AD 2016–25–26] 

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 all The 

Boeing Company Model MD–90–30 

airplanes. This AD was prompted by 

reports of stick shaker activation at 

airspeeds that were above the stall 

protection system’s stick shaker 

schedule. This AD requires installing 

angle-of-attack (AOA) sensor external 

case heaters on the existing AOA 

sensors, installing additional wires, and 

doing a functional test and applicable 

corrective actions. We are issuing this 

AD to address the unsafe condition on 

these products. 

DATES: This AD is effective February 2, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 2, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Contractual & Data Services 

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

110–SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; 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– 

6898. 

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– 

6898; 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: Eric 

Igama, Aerospace Engineer, Systems 

and Equipment Branch, ANM–130L, 

FAA, Los Angeles Aircraft Certification 

Office (ACO), 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5388; fax: 562–627– 

5210; email: roderick.igama@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 all The Boeing Company Model 

MD–90–30 airplanes. The NPRM 

published in the Federal Register on 

June 13, 2016 (81 FR 38113) (‘‘the 

NPRM’’). The NPRM was prompted by 

reports of stick shaker activation at 

airspeeds that were above the stall 

protection system’s stick shaker 

schedule. The NPRM proposed to 

require installing AOA sensor external 

case heaters on the existing AOA 

sensors, installing additional wires, and 

doing a functional test and applicable 

corrective actions. We are issuing this 

AD to prevent ice formation between the 

AOA sensor vane and face plate, which 

could cause both vanes to become 

immobilized. If both vanes become 

immobilized, the stall protection system 

could become unreliable or nonfunctional, which could result in loss of 

control of the airplane. 

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. 

Support of the NPRM 

The Air Line Pilots Association, 

International provided comments that 

supported the intent of the NPRM. 

Request To Change Boeing Address 

Identified in the NPRM 

Boeing asked that we change its 

mailing address for obtaining copies of 

service information as specified in the 

NPRM to the following: Boeing 

Commercial Airplanes, Attention: 

Contractual & Data Services (C&DS), 

2600 Westminster Blvd., MC 110–SK57, 

Seal Beach, CA 90740–5600; telephone 

562–797–1092; Internet https://

www.myboeingfleet.com. Boeing stated 

that this address is valid for this and all 

future ADs affecting Boeing airplanes. 

We agree with the commenter’s 

request. We have updated the contact 

information accordingly. However, we 

have corrected the telephone number; it 

should be 562–797–1717. We have 

changed this AD to include this new 

mailing address for Boeing service 

information. 

Request To Clarify Certain Language in 

the NPRM 

Boeing asked that we clarify the 

language specifying what prompted the 

AD action, and the description of the 

unsafe condition, as specified in the 

SUMMARY section. Boeing stated that the 

reported incident occurred ‘‘on Model 

717–200 airplanes’’ and included 

further description of what prompted 

the AD action. Boeing also stated that 

including this description clarifies the 

airplane model on which the safety 

issue was identified. Boeing also asked 

that we revise the description of the 

unsafe condition, which stated that ‘‘the 

vane’’ could become immobilized. 

Boeing noted that the safety issue is a 

common cause failure (both vanes could 

become immobilized) due to an external 

threat (i.e., weather). 

We agree to add ‘‘both vanes’’ to the 

Discussion section and paragraph (e) of 

this AD for clarification. Information 

concerning the origin of the safety issue 

on Model 717–200 airplanes was 

included in the Discussion section of 

the NPRM. Since the information in the 

Discussion section of the NPRM does 

not reappear in the final rule, we have 

not changed this AD in this regard. In 

addition, we do not agree that the 

requested changes are necessary in the 

SUMMARY section, which merely 

provides a high-level description of the 

relevant information. Details concerning 

the unsafe condition that appeared in 

the SUMMARY section of the NPRM have 

been removed from this final rule in 

response to new guidance from the 

Office of the Federal Register. 

Boeing also asked that we clarify the 

AD requirements by specifying 

‘‘installing additional wires’’ in lieu of 

‘‘changing wires’’ and installing AOA 

sensor external case heaters ‘‘on the 

AOA sensors’’ in lieu of ‘‘and AOA 

sensors.’’ Delta Air Lines (Delta) asked 

that we change ‘‘and AOA sensors’’ to 


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