Federal Register / Vol. 83, No. 10 / Tuesday, January 16, 2018 / Rules and Regulations 2039 

telephone 425–227–2432; facsimile 

425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Background 

On April 22, 2016, the Federal 

Register published a document 

designated as Docket No. FAA–2015– 

4279, Final Special Conditions No. 25– 

612–SC (81 FR 23573). The document 

issued special conditions pertaining to 

the installation of non-rechargeable 

lithium batteries in Gulfstream GVI 

airplanes. As published, the document 

contained an error in a title 14, Code of 

Federal Regulations (14 CFR) section 

citation in two locations in the final 

special conditions document. These 

citations inadvertently referred to the 

wrong amendment level for the 

certification basis of the various 

Gulfstream GVI airplanes. Therefore, we 

have corrected these special conditions 

to include the correct citations and 

amendment levels that apply to 

certification bases applicable to 

airplanes with non-rechargeable 

lithium-ion battery installations. 

Correction 

In the final special conditions 

document (FR Doc. 2016–09311 Filed 

4–21–16; 8:45 a.m.), published on April 

22, 2016 (81 FR 23573), make the 

following corrections. 

1. On page 23574, second column, 

change the following paragraph: 

These special conditions apply to all 

non-rechargeable lithium battery 

installations in lieu of § 25.1353(b)(1) 

through (b)(4) at Amendment 25–113. 

Sections 25.1353(b)(1) through (b)(4) at 

Amendment 25–113 remain in effect for 

other battery installations. 

To read: 

These special conditions apply to all 

non-rechargeable lithium battery 

installations in lieu of § 25.1353(b)(1) 

through (4) at Amendment 25–123 or 

§ 25.1353(c)(1) through (4) at earlier 

amendments. Those regulations remain 

in effect for other battery installations. 

2. On page 23577, third column, 

change the following paragraph: 

In lieu of § 25.1353(b)(1) through 

(b)(4) at Amendment 25–113, each nonrechargeable lithium battery installation 

must: 

To read: 

In lieu of § 25.1353(b)(1) through (4) 

at Amendment 25–123, or 

§ 25.1353(c)(1) through (4) at earlier 

amendments, each non-rechargeable 

lithium battery installation must: 

Issued in Renton, Washington, on January 

9, 2018. 

Victor Wicklund, 

Manager, Transport Standards Branch, Policy 

and Innovation Division, Aircraft 

Certification Service. 

[FR Doc. 2018–00547 Filed 1–12–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0826; Product 

Identifier 2016–SW–084–AD; Amendment 

39–19153; AD 2018–01–12] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2015–22– 

53 for Airbus Helicopters Model 

AS350B3 helicopters. AD 2015–22–53 

required revising the rotorcraft flight 

manual (RFM) to perform the yaw load 

compensator check after rotor shutdown and to state that the yaw servo 

hydraulic switch must be in the ‘‘ON’’ 

position before taking off. Since we 

issued AD 2015–22–53, Airbus 

Helicopters developed a modification of 

the ACCU TST switch. This new AD 

retains the requirements of AD 2015– 

22–53 and requires modifying the yaw 

servo hydraulic switch (collective 

switch) and replacing the ACCU TST 

button. The actions of this AD are 

intended to address an unsafe condition 

on these products. 

DATES: This AD is effective February 20, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 20, 2018. 

ADDRESSES: For Airbus Helicopters 

service information identified in this 

final rule, contact Airbus Helicopters, 

2701 N. Forum Drive, Grand Prairie, TX 

75052; telephone (972) 641–0000 or 

(800) 232–0323; fax (972) 641–3775; or 

at http://www.helicopters.airbus.com/ 

website/en/ref/Technical-Support_

73.html. You may view this referenced 

service information at the FAA, Office 

of the Regional Counsel, Southwest 

Region, 10101 Hillwood Pkwy., Room 

6N–321, Fort Worth, TX 76177. It is also 

available on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0826. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at http://

www.regulations.gov in Docket No. 

FAA–2017–0826; 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 Section, 

Rotorcraft Standards Branch, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; 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 2015–22–53, 

Amendment 39–18331 (80 FR 74982, 

December 1, 2015) and add a new AD. 

AD 2015–22–53 applied to Airbus 

Helicopters Model AS350B3 helicopters 

with a dual hydraulic system installed. 

AD 2015–22–53 required revising the 

pre-flight and post-flight procedures in 

the RFM to perform the yaw load 

compensator check (ACCU TST switch) 

after rotor shut-down instead of during 

preflight procedures and to state that the 

yaw servo hydraulic switch (collective 

switch) must be in the ‘‘ON’’ (forward) 

position before taking off. 

The NPRM published in the Federal 

Register on September 8, 2017 (82 FR 

42487). The NPRM was prompted by 

AD No. 2016–0220, dated November 4, 

2016, issued by EASA, which is the 

Technical Agent for the Member States 

of the European Union, to correct an 

unsafe condition for Airbus Helicopters 

Model AS 350 B3 helicopters. EASA 

advises that further analysis resulted in 

the recognition that a pilot could forget 

to activate a switch despite the RFM 

changes and that altering the bistable 

push button (push-on, push-off) ACCU 

TST switch is necessary. 

Accordingly, the NPRM proposed to 

retain the requirements of AD 2015–22– 

53 and also proposed to require, within 


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2040 Federal Register / Vol. 83, No. 10 / Tuesday, January 16, 2018 / Rules and Regulations 

350 hours time-in-service, installing a 

timer relay for the yaw servo hydraulic 

switch, installing an additional light on 

the caution and warning panel, and 

replacing the bistable ACCU TST button 

with a monostable button. The proposed 

requirements were intended to prevent 

takeoff without hydraulic pressure in 

the tail rotor (T/R) hydraulic system, 

loss of T/R flight control, and 

subsequent loss of control of the 

helicopter. 

Comments 

After our NPRM was published, we 

received comments from two 

commenters. 

Requests 

The National Transportation Safety 

Board (NTSB) requested that the AD 

address the need for an alert when there 

is insufficient pressure in the T/R 

hydraulic system, which results in 

increased pedal loads. In support of this 

request, the NTSB stated that, for at 

least four events it investigated in which 

the yaw servo hydraulic switch was 

likely not returned to its correct position 

before takeoff, a salient alert could have 

cued the pilots of insufficient T/R 

hydraulic pressure. 

We partially agree. We agree that an 

aural and visual alert to the pilot to 

indicate loss of T/R hydraulic pressure 

would address this unsafe condition. 

However, Airbus Helicopters has not 

developed an alteration that provides 

such an alert. The FAA has determined 

the requirements proposed by the 

NPRM are appropriate to address this 

unsafe condition at this time. Should an 

aural and visual alert to the pilot to 

indicate loss of T/R hydraulic pressure 

be developed and approved, we might 

consider additional rulemaking at that 

time. We did not change the AD based 

on this comment. 

The NTSB also requested that we 

eliminate the requirement to move the 

yaw load compensator check (ACCU 

TST switch) to post-flight procedures 

instead of preflight procedures. In 

support of this request, the NTSB stated 

that performing this check post-flight 

does not ensure the yaw load 

compensator will remain functional for 

the next flight. 

We disagree. We determined that 

requiring this check post-flight with the 

RFM procedure to have the yaw servo 

hydraulic switch in the ‘‘ON’’ position 

before takeoff, along with the alterations 

to the yaw servo hydraulic switch and 

replacement of the ACCU TST button, 

reduces the risk of takeoff with the 

switch in the incorrect position to an 

acceptable level. We did not change the 

AD based on this comment. 

Eagle Copters requested we change 

the AD to address helicopters that have 

replaced the factory console with a 

Geneva Aviation P122 or P132 electrical 

console under Eagle Copters USA, Inc. 

Supplemental Type Certificate No. 

SH4747NM. In support of this request, 

Eagle Copters noted that operators of 

these helicopters will need to request an 

Alternative Method of Compliance to 

comply with the AD, because the Airbus 

Helicopters service information required 

for replacing the bistable ACCU TST 

button does not apply to these 

helicopters. Eagle Copters proposed 

adding a requirement to the AD to 

replace the HYD TEST/ACCU TEST 

ESN–11 switch on the console from the 

locking bistable toggle switch to a 

locking momentary (monostable) toggle 

switch part number (P/N) MS24658– 

16F. 

We agree. We revised the AD to 

require helicopters with a P122 or P132 

electrical console installed to replace 

the bistable ACCU TEST switch (which 

may be marked ‘‘HYD TEST’’) with 

monostable toggle switch P/N 

MS24658–16F. 

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 

the same type design and that air safety 

and the public interest require adopting 

the AD requirements as proposed with 

the change previously described. This 

change is consistent with the intent of 

the proposals in the NPRM and will not 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Airbus Helicopters 

Service Bulletin (SB) No. AS350– 

67.00.64, Revision 0, dated February 25, 

2015. This service information specifies 

procedures to install a timer relay and 

an additional indicator light on the 

caution and warning panel. This 

modification provides an ‘‘OFF’’ status 

indication of the yaw servo hydraulic 

switch by flashing a newly installed 

‘‘HYD2’’ indicator light on the caution 

and warning panel. Airbus Helicopters 

identifies performance of this SB as 

modification 074622. This modification 

was available when AD 2015–22–53 was 

issued; however, it was determined 

unnecessary to address the unsafe 

condition at that time. 

We also reviewed Airbus Helicopters 

SB No. AS350–67.00.65, Revision 0, 

dated August 25, 2016. This service 

information specifies procedures to 

replace the bistable push button ACCU 

TST switch with a monostable push 

button switch. Airbus Helicopters 

identifies performance of this SB as 

modification 074719. 

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. 

Other Related Service Information 

We reviewed Airbus Helicopters SB 

No. AS350–67.00.66, Revision 1, dated 

October 22, 2015. This service 

information specifies inserting specific 

pages of the SB into the rotorcraft flight 

manual. These pages revise the preflight 

and post-flight hydraulic checks by 

moving the T/R yaw load compensator 

check from preflight to post-flight. 

These pages also revise terminology 

within the flight manuals for the 

different engine configurations. 

Costs of Compliance 

We estimate that this AD affects 86 

helicopters of U.S. Registry. We estimate 

that operators may incur the following 

costs in order to comply with this AD. 

Labor costs are estimated at $85 per 

work-hour. 

Revising an RFM would take about 

0.5 work-hour for a cost of $43 per 

helicopter and $3,698 for the U.S. fleet. 

Installing a timer relay for the yaw servo 

hydraulic switch and an indicator light 

would take about 9 work-hours and 

parts would cost about $2,224. 

Replacing the ACCU TST button would 

take about 1 work-hour and parts would 

cost about $2,244. 

Based on these figures, we estimate a 

total cost of $5,361 per helicopter and 

$461,046 for the U.S. fleet. 

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 


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Federal Register / Vol. 83, No. 10 / Tuesday, January 16, 2018 / Rules and Regulations 2041 

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, 

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) 

2015–22–53, Amendment 39–18331 (80 

FR 74982, December 1, 2015), and 

adding the following new AD: 

2018–01–12 Airbus Helicopters: 

Amendment 39–19153; Docket No. 

FAA–2017–0826; Product Identifier 

2016–SW–084–AD. 

(a) Applicability 

This AD applies to Model AS350B3 

helicopters with a dual hydraulic system 

installed, certificated in any category. 

Note 1 to paragraph (a) of this AD: The 

dual hydraulic system for Model AS350B3 

helicopters is referred to as Airbus 

modification OP 3082 or OP 3346. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

lack of hydraulic pressure in a tail rotor 

(T/R) hydraulic system. This condition could 

result in loss of T/R flight control and 

subsequent loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2015–22–53, 

Amendment 39–18331 (80 FR 74982, 

December 1, 2015). 

(d) Effective Date 

This AD becomes effective February 20, 

2018. 

(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 further flight, insert a copy of 

this AD into the rotorcraft flight manual, 

Section 4 Normal Operating Procedures, or 

make pen and ink changes to the preflight 

and post-flight procedures as follows: 

(i) Stop performing the yaw load 

compensator check (ACCU TST switch) 

during preflight procedures, and instead 

perform the yaw load compensator check 

during post-flight procedures after rotor shutdown. 

(ii) The yaw servo hydraulic switch 

(collective switch) must be in the ‘‘ON’’ 

(forward) position before takeoff. 

Note 2 to paragraph (f)(1)(ii) of this AD: 

The yaw servo hydraulic switch is also called 

the hydraulic pressure switch or hydraulic 

cut off switch in various Airbus Helicopters 

rotorcraft flight manuals. 

(2) Within 350 hours time-in-service: 

(i) Install a timer relay for the yaw servo 

hydraulic switch (collective switch) by 

following the Accomplishment Instructions, 

paragraph 3.B.2.b.1, 3.B.2.b.2, 3.B.2.b.3, 

3.B.2.b.4, 3.B.2.b.5, or 3.B.2.b.6, as applicable 

to the configuration of your helicopter, of 

Airbus Helicopters Service Bulletin (SB) No. 

AS350–67.00.64, Revision 0, dated February 

25, 2015 (AS350–67.00.64). If your helicopter 

has an automatic pilot system, also comply 

with paragraph 3.B.2.b.7 of AS350–67.00.64. 

(ii) Install an indicator light on the caution 

and warning panel by following the 

Accomplishment Instructions, paragraph 

3.B.2.c.1 or 3.B.2.c.2, as applicable to the 

configuration of your helicopter, of AS350– 

67.00.64. 

(iii) For helicopters with a Geneva Aviation 

P122 or P132 electrical console installed, 

replace the ESN–11 HYD TEST (ACCU TST) 

switch with a monostable toggle switch part 

number MS24658–16F. 

(iv) For helicopters without a Geneva 

Aviation P122 or P132 electrical console 

installed, replace the bistable ACCU TST 

button on the control panel with a 

monostable button as depicted in Figure 1 or 

Figure 3, as applicable to the configuration of 

your helicopter, of Airbus Helicopters SB No. 

AS350–67.00.65, Revision 0, dated August 

25, 2016. 

(3) After the effective date of this AD, do 

not install a bistable ACCU TST button on 

any helicopter. 

(g) Special Flight Permits 

A special flight permit may be issued for 

paragraph (f)(2) of this AD only. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Section, Rotorcraft Standards Branch, FAA, 

may approve AMOCs for this AD. Send your 

proposal to: George Schwab, Aviation Safety 

Engineer, Safety Management Section, 

Rotorcraft Standards Branch, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@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 

(1) Airbus Helicopters SB No. AS350– 

67.00.66, Revision 1, dated October 22, 2015, 

which is not incorporated by reference, 

contains additional information about the 

subject of this AD. For service information 

identified in this AD, contact Airbus 

Helicopters, 2701 N. Forum Drive, Grand 

Prairie, TX 75052; telephone (972) 641–0000 

or (800) 232–0323; fax (972) 641–3775; or at 

http://www.helicopters.airbus.com/website/ 

en/ref/Technical-Support_73.html. You may 

view a copy of the service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy, 

Room 6N–321, Fort Worth, TX 76177. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2016–0220, dated November 4, 2016. 

You may view the EASA AD on the internet 

at http://www.regulations.gov in Docket No. 

FAA–2017–0826. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2910, Main Hydraulic System. 

(k) 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 Service Bulletin No. 

AS350–67.00.64, Revision 0, dated February 

25, 2015. 

(ii) Airbus Helicopters Service Bulletin No. 

AS350–67.00.65, Revision 0, dated August 

25, 2016. 

(3) For Airbus Helicopters service 

information identified in this AD, contact 

Airbus Helicopters, 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone (972) 

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

3775; or at http://www.helicopters.

airbus.com/website/en/ref/TechnicalSupport_73.html. 

(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. 


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(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 Fort Worth, Texas, on January 8, 

2018. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2018–00478 Filed 1–12–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0514; Product 

Identifier 2016–NM–206–AD; Amendment 

39–19148; AD 2018–01–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A300 B4–600, B4–600R, 

and F4–600R series airplanes, and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes) airplanes. 

This AD was prompted by a revision of 

certain airworthiness limitation item 

(ALI) documents, which require more 

restrictive maintenance requirements 

and airworthiness limitations. This AD 

requires revising the maintenance or 

inspection program, as applicable, to 

incorporate new maintenance 

requirements and airworthiness 

limitations. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective February 20, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 20, 2018. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus SAS, Airworthiness Office— 

EAW, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone 

+33 5 61 93 36 96; fax +33 5 61 93 44 

51; email account.airworth-eas@

airbus.com; internet http://

www.airbus.com. You may view this 

referenced service information at the 

FAA, Transport Standards Branch, 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–2017– 

0514. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0514; 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 street address for 

the Docket Office (telephone 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: Dan 

Rodina, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 1601 Lind 

Avenue SW, Renton, WA 98057–3356; 

telephone 425–227–2125; fax 425–227– 

1149. 

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 Airbus Model A300 B4–600, 

B4–600R, and F4–600R series airplanes, 

and Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes). The NPRM 

published in the Federal Register on 

June 2, 2017 (82 FR 25552) (‘‘the 

NPRM’’). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2016–0218, 

dated November 2, 2016 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus Model A300 B4–600, B4– 

600R, and F4–600R series airplanes, and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes). The MCAI 

states: 

The airworthiness limitations for Airbus 

A300–600 aeroplanes, which are approved by 

EASA, are currently defined and published 

in the Airbus A300–600 Airworthiness 

Limitations Section (ALS) document(s). 

These instructions have been identified as 

mandatory actions for continued 

airworthiness. 

Failure to accomplish these instructions 

could result in an unsafe condition. 

EASA previously issued [EASA] AD 2014– 

0124 (later revised) [which includes actions 

for Airbus A300–600 airplanes; those actions 

are included in FAA AD 2013–13–13, 

Amendment 39–17501 (79 FR 48957, August 

19, 2014) (‘‘AD 2013–13–13’’)], requiring the 

actions described in Airbus A300–600 

Airworthiness Limitation Item (ALI) 

Document at issue 13 and Temporary 

Revision (TR) 13.1. 

Since EASA AD 2014–0124R1 was issued, 

Airbus replaced A300–600 ALI Document 

issue 13, with A300–600 ALS Part 2 Revision 

01 and then published the A300–600 ALS 

Part 2 Variation 1.1 and Variation 1.2, to 

introduce more restrictive maintenance 

requirements and/or airworthiness 

limitations. 

A300–600 ALS Part 2 Variation 1.1 also 

includes ALI 571067 and ALI 571068, 

superseding Service Bulletin A300–53–6154, 

which is referenced in EASA AD 2006–0257 

[which corresponds to FAA AD 2007–22–05, 

Amendment 39–15241 (72 FR 60236, October 

24, 2007) (‘‘AD 2007–22–05’’)]. 

For the reasons described above, this 

[EASA] AD retains part of the requirements 

of EASA AD 2014–0124R1, which will be 

superseded, and requires accomplishment of 

the actions specified in Airbus A300–600 

ALS Part 2 Revision 01, and ALS Part 2 

Variation 1.1 and ALS Part 2 Variation 1.2 

(hereafter collectively referred to as ‘the ALS’ 

in this [EASA] AD), and supersedes EASA 

AD 2006–0257. The remaining requirements 

of EASA AD 2014–0124R1 are retained in AD 

2016–0217, applicable to A310 aeroplanes, 

published at the same time as this [EASA] 

AD. 

You may examine the MCAI in the 

AD docket on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0514. 

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. FedEx generally supported the 

NPRM. 

Request To Provide an Additional 

Compliance Time Grace Period 

United Parcel Service (UPS) requested 

that the compliance time specified in 

paragraph (g) of the NPRM be revised to 

add an additional grace period. UPS 

pointed out that there are several new 

or revised tasks with relatively low 

compliance time thresholds that would 

lead to short lead times on 

accomplishing those tasks after the 

effective date of the AD. UPS referenced 

the compliance time required in AD 


daltland on DSKBBV9HB2PROD with RULES