Federal Register / Vol. 83, No. 181 / Tuesday, September 18, 2018 / Rules and Regulations 47047 

(3) For Models 35, 35A, 36, and 36A 

airplanes: Within 24 months after October 

23, 2018 (the effective date of this AD) or 

within 400 landings after October 23, 2018 

(the effective date of this AD), whichever 

occurs first, replace the nose roller fitting, 

nose roller support bracket, and adjacent rib 

support structure with replacement parts by 

following the Accomplishment Instructions 

in Bombardier Learjet 35/36 SB 35/36–27–50 

Recommended, dated September 11, 2017. 

(4) For Models 55, 55B, and 55C airplanes: 

Within 24 months after October 23, 2018 (the 

effective date of this AD) or within 400 

landings after October 23, 2018 (the effective 

date of this AD), whichever occurs first, 

replace the nose roller fitting, nose roller 

support bracket, and adjacent rib support 

structure with replacement parts by 

following the Accomplishment Instructions 

in Bombardier Learjet 55 SB 55–27–41 

Recommended, dated September 11, 2017. 

(5) For Model 60 airplanes: Within 12 

months after October 23, 2018 (the effective 

date of this AD) or within 200 landings after 

October 23, 2018 (the effective date of this 

AD), whichever occurs first, replace the nose 

roller fitting, nose roller support bracket, and 

adjacent rib support structure with 

replacement parts by following the 

Accomplishment Instructions in Bombardier 

Learjet 60 SB 60–27–39 Recommended, 

Revision 1, dated January 15, 2018. 

(6) For all airplanes: Some compliance 

times in this AD are presented in landings. 

If you do not keep a record of the total 

number of landings, then use a 1-to-1 

conversion for hours time-in-service (TIS) to 

landings. Example: 20 hours TIS = 20 

landings. 

(7) For Models 31, 31A, 35, 35A, 36, 36A, 

55, 55B, 55C, and 60 airplanes: Although 

Paragraph 3.B.(2) of the applicable SB for 

these models that have modified flap roller 

assemblies requires the operator to contact 

Learjet Inc. for repair instructions, this AD 

requires you do the repair using a method 

approved by the Manager, Wichita ACO 

Branch, FAA. For a repair method to be 

approved by the Manager, Wichita ACO 

Branch, as required by this paragraph, the 

Manager’s approval letter must specifically 

refer to this AD. 

(h) Credit for Previous Actions 

For Model 60 airplanes: This AD allows 

credit for actions required in paragraph (g)(5) 

of this AD if done before the effective date 

of this AD following Bombardier Learjet 60 

SB 60–27–39 Recommended, Basic Issue, 

dated September 11, 2017. 

(i) No Reporting Requirement 

Although Bombardier Learjet 28/29 SB 28/ 

29–27–31 Recommended, dated September 

11, 2017; Bombardier Learjet 31 SB 31–27– 

35 Recommended, dated September 11, 2017; 

Bombardier Learjet 35/36 SB 35/36 –27–50 

Recommended, dated September 11, 2017; 

Bombardier Learjet 55 SB 55–27–41 

Recommended, dated September 11, 2017; 

and Bombardier Learjet 60 SB 60–27–39 

Recommended, Revision 1, dated January 15, 

2018, all specify to submit a compliance 

response form to the manufacturer per 

paragraph 3.E., this AD does not require that 

action. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita ACO branch, 

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 

certification office, send it to the attention of 

the person identified in paragraph (k)(1) 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. 

(k) Related Information 

For more information about this AD, 

contact Tara Shawn, Aerospace Engineer, 

Wichita ACO Branch, 1801 Airport Road, 

Room 100, Wichita, Kansas 67209; telephone: 

(316) 946–4141; fax: (316) 946–4107; email: 

tara.shawn@faa.gov or Wichita-COS@faa.gov. 

(l) 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) Bombardier Learjet 28/29 Service 

Bulletin (SB) 28/29–27–31 Recommended, 

dated September 11, 2017; 

(ii) Bombardier Learjet 31 SB 31–27–35 

Recommended, dated September 11, 2017; 

(iii) Bombardier Learjet 35/36 SB 35/36 

–27–50 Recommended, dated September 11, 

2017; 

(iv) Bombardier Learjet 55 SB 55–27–41 

Recommended, dated September 11, 2017; 

and 

(v) Bombardier Learjet 60 SB 60–27–39 

Recommended, Revision 1, dated January 15, 

2018. 

(3) For service information identified in 

this AD, contact Learjet, Inc., One Learjet 

Way, Wichita, Kansas 67209; telephone: 316– 

946–2000; email: ac.ict@

aero.bombardier.com; internet: https://

www.bombardier.com. 

(4) You may view this service information 

at the FAA, Policy and Innovation Division, 

901 Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. In 

addition, you can access this service 

information on the internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2017–1078. 

(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 Kansas City, Missouri, on August 

31, 2018. 

Melvin J. Johnson, 

Deputy Director, Policy & Innovation Division, 

Aircraft Certification Service. 

[FR Doc. 2018–19853 Filed 9–17–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0390; Product 

Identifier 2017–NM–130–AD; Amendment 

39–19397; AD 2018–18–18] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

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 SAS Model A300 series 

airplanes. This AD was prompted by a 

revision of an airworthiness limitation 

items (ALI) document. This AD requires 

revising the maintenance or inspection 

program, as applicable, to incorporate 

the specified maintenance requirements 

and airworthiness limitations. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective October 23, 

2018. 

ADDRESSES: 

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–2018– 

0390; or in person at Docket Operations 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this final rule, 

the regulatory evaluation, any 

comments received, and other 

information. The address for Docket 

Operations (phone: 800–647–5527) is 

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, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3225. 

SUPPLEMENTARY INFORMATION: 


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47048 Federal Register / Vol. 83, No. 181 / Tuesday, September 18, 2018 / Rules and Regulations 

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 SAS Model A300 

series airplanes. The NPRM published 

in the Federal Register on May 11, 2018 

(83 FR 21955). The NPRM was 

prompted by a revision of an ALI 

document. The NPRM proposed to 

require revising the maintenance or 

inspection program, as applicable, to 

incorporate the specified maintenance 

requirements and airworthiness 

limitations. 

We are issuing this AD to address the 

reduced structural integrity of the 

airplane and possible loss of 

controllability of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2017–0145, 

dated August 31, 2017 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus SAS Model A300 series 

airplanes. The MCAI states: 

Some airworthiness limitations previously 

defined in A300 ALS [Airworthiness 

Limitations Section] Part 1 have been 

removed from that document and should 

normally be included in an ALS Part 4. 

Airbus does not plan to issue an ALS Part 4 

for A300 aeroplanes. 

Nevertheless, failure to comply with these 

airworthiness limitations could result in an 

unsafe condition. 

For the reason described above, it has been 

decided to require the application of these 

airworthiness limitations through a separate 

AD. 

Previously, EASA issued AD 2013–0210 

[which corresponds to FAA AD 2014–16–13, 

Amendment 39–17937 (79 FR 51083, August 

27, 2014) (‘‘AD 2014–16–13’’)] to require 

implementation of airworthiness limitations 

applicable to main landing gear (MLG) barrel 

assembly, retraction actuator assembly, 

linkage assembly and flanged duct, which 

were previously defined in Revision 00 of 

A300 ALS Part 1 but removed from Revision 

01 of A300 ALS Part 1, adding those limits 

as an Appendix to the AD. 

Since EASA AD 2013–0210 was issued, 

improvement of safe life component selection 

resulted, among others, in removal of 15 nose 

landing gear (NLG) parts from Revision 02 of 

A300 ALS Part 1. 

Consequently, this [EASA] AD retains the 

requirements of EASA AD 2013–0210, which 

is superseded, and requires, in addition to 

the implementation of airworthiness 

limitations already contained in EASA AD 

2013–0210, the implementation of 

airworthiness limitations applicable to NLG 

barrel assembly and shock absorber 

assembly, previously contained in Revision 

01 of A300 ALS Part 1, as specified in 

Appendix 1 of this 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–2018– 

0390. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

The following presents the comment 

received on the NPRM and the FAA’s 

response to the comment. 

Request To Supersede AD 2014–16–13 

Airbus questioned the need to keep 

AD 2014–16–13 and whether the 

proposed AD should instead supersede 

AD 2014–16–13. Airbus noted that the 

proposed AD lists all of the ALIs in 

EASA AD 2017–0145, dated August 31, 

2017, not just the ALIs that have been 

updated since we issued AD 2014–16– 

13. We infer that Airbus wanted the 

proposed AD changed to a supersedure 

AD. 

We disagree with the request to 

change this AD to a supersedure AD. To 

address the unsafe condition, we chose 

to match EASA AD 2017–0145, dated 

August 31, 2017, and include the same 

ALIs. Because accomplishment of the 

requirements of this AD terminates all 

requirements of AD 2014–16–13, a 

supersedure is not necessary. We have 

not changed this AD in this regard. 

Request To Release Related ADs at the 

Same Time 

Airbus requested that we release this 

final rule at the same time as the 

following related ADs to provide clarity 

to operators. All four pending ADs are 

related to the same removal of 15 nose 

landing gear parts from ALS Part 1, on 

different airplane models. 

• Docket No. FAA–2018–0364, 

Product Identifier 2017–NM–154–AD 

(EASA AD 2017–0204, dated October 

12, 2017). 

• Docket No. FAA–2018–0365, 

Product Identifier 2017–NM–155–AD 

(EASA AD 2017–0203, dated October 

12, 2017). 

• Docket No. FAA–2018–0396, 

Product Identifier 2017–NM–156–AD 

(EASA AD 2017–0202, dated October 

12, 2017). 

We agree with the request insofar as 

we can control the publication 

schedule. While we cannot ensure that 

all four will be published on the same 

date, we will coordinate with the Office 

of the Federal Register (OFR) and 

attempt to issue all four final rules at the 

same time. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this 

final rule 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 

addressing 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 final rule. 

Costs of Compliance 

We estimate that this AD affects 5 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

We have determined that revising the 

maintenance or inspection program 

takes an average of 90 work-hours per 

operator, although we recognize that 

this number may vary from operator to 

operator. In the past, we have estimated 

that this action takes 1 work-hour per 

airplane. Since operators incorporate 

maintenance or inspection program 

changes for their affected fleet(s), we 

have determined that a per-operator 

estimate is more accurate than a perairplane estimate. Therefore, we 

estimate the total cost per operator to be 

$7,650 (90 work-hours × $85 per workhour). 

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. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 


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Federal Register / Vol. 83, No. 181 / Tuesday, September 18, 2018 / Rules and Regulations 47049 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to transport category 

airplanes and associated appliances to 

the Director of the System Oversight 

Division. 

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 

the 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): 

2018–18–18 Airbus SAS: Amendment 39– 

19397; Docket No. FAA–2018–0390; 

Product Identifier 2017–NM–130–AD. 

(a) Effective Date 

This AD is effective October 23, 2018. 

(b) Affected ADs 

This AD affects AD 2014–16–13, 

Amendment 39–17937 (79 FR 51083, August 

27, 2014) (‘‘AD 2014–16–13’’). 

(c) Applicability 

This AD applies to Airbus SAS Model 

A300 B2–1A, B2–1C, B2K–3C, B2–203, B4– 

2C, B4–103, and B4–203 airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Time Limits/Maintenance 

Checks. 

(e) Reason 

This AD was prompted by a revision of an 

airworthiness limitation items (ALI) 

document. We are issuing this AD to prevent 

reduced structural integrity of the airplane 

and possible loss of controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revision of Maintenance or Inspection 

Program 

Within 90 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate the 

safe life limits included in figure 1 to 

paragraph (g) of this AD. The initial 

compliance time for the replacements is prior 

to the applicable life limits specified in figure 

1 to paragraph (g) of this AD, or within 90 

days after the effective date of this AD, 

whichever occurs later. The term ‘‘FH’’ in 

figure 1 to paragraph (g) of this AD means 

total flight hours. The term ‘‘LDG’’ in figure 

1 to paragraph (g) of this AD means total 

airplane landings. 

BILLING CODE 4910–13–P 


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Figure 1 to paragraph (g) of this AD- New Life Limits for the Main Landing Gear 

(MLG) Barrel Assembly, Retraction Actuator Assembly, Linkage Assembly; Pneumatic 

Flange Duct; Nose Landing Gear (NLG) Barrel Assembly and Shock Absorber Assembly 

SAFE LIFE LIMITS (*) Affected Model(s) 

Part Name Part Number FH LOG Cal B2-1A 82K-3C 82-320 B4-2C 84_2xx C4-203 

B2-1C B2-20x B4-1xx F4-203 

ATA 32-1~0 MAIN LANDING GEAR 

BARREL ASSEMBLY 

C66277-10 NJA 66600 N/A X X X X 

C66277-12 NJA 76600 N/A X X X X 

Stirrup C66277-14 NJA 76600 N/A X X X X 

058303-1 N/A 76600 N/A X X X X 

C66457 N/A 76600 N/A X X X X 

048939 NJA 76600 N/A X X X X 

Stirrup pin 048939-1 N/A 76600 N/A X X X X 

058314-1 NJA 76600 N/A X X X X 

C66279 NJA 76600 N/A X X X X 

C66279-2 NJA 76600 N/A X X X X 

Universal joint C66279-6 NJA 76600 N/A X X X X 

058313-1 NJA 76600 N/A X X X X 

C61637-10 N/A 76600 N/A X X 

Plate (Upper C61637-11 NJA 76600 N/A X X end) 

C61637-12 N/A 76600 N/A X X 

C61638-10 N/A 53300 N/A X X 

Plate (Rear head C61638-11 N/A 53300 N/A X X end) 

C61638-20 NJA 76600 N/A X X 

Tie rod C68523-3 NJA 76600 N/A X X 

RETRACTION ACTUATOR ASSEMBLY 

(1) When SB Al00-32-0123 embodied before SB Al00-32-0113. 

I (2) When SB AJ00-32..0123 embodied after SB Al00-32..0113. 

C69028-1 N/A 34000 N/A X X 

C69028-4 N/A 34000 N/A X X 

C69029-1 (1) N/A 32000 N/A X X X X 

Sliding rod 

C69029-2 N/A 32000 N/A X X X X 

C69029-3 N/A 32000 N/A X X X X 

C69029-4 (2) N/A 22000 N/A X X X X 

C67078 NJA 33000 N/A X X X X 

Piston 

C67078-1 N/A 33000 N/A X X X X 

C61342-4 NJA 36700 N/A X X 

End fitting C66510-4 NJA 32000 N/A X X X X 
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LINKAGE ASSEMBLY 

Upper C61505 NIA 76600 N/A X X 

multiple link C61505-1 NIA 76600 N/A X X pin (Multiple 

link/Upper 

linkS C61505-20 NIA 76600 NIA X X 

ATA36-11-05 PNEUMATIC 

(1) "xx" at the end of the PIN stands for anv number between 00 and 99. 

Duct flanged ( 1 ) A2127 ~~63000 N/A 24000 N/A X X X 

ATA32-20-00 NOSE LANDING GEAR 

BARREL ASSEMBLY (FIG.07) 

(1) Limitation applicable to WV01 & WV03 only. 

(2) Part must be replaced by a new one every time it is removed from the barrel. 

(3) The nut must be replaced by a new one every time it is removed from the pin. When the nut is 

temporarily removed and reinstalled for the purpose of performing maintenance outside a workshop, no 

replacement is required provided the nut's removal and reinstallation are performed on the same pin and 

neither the pin nor the nut accumulates time in service during the period between the removal and 

reinstallation. 

End fitting 068062 N/A (2) N/A X X X X X X 

pin nut MS17825-6 N/A (2) N/A X X X X X X 

AN6-17 N/A (2) N/A X X X X X X 

End fitting pin 061183 N/A (2) N/A X X X X X X 

068063 N/A (2) N/A X X X X X X 

NAS1306-22D N/A (2) N/A X X X X X X 

C62032 N/A 65700 N/A X X X X X X 

C62032-1 N/A 65700 N/A X X X X X X 

C62032-2 N/A 65700 N/A X X X X X X 

End fitting C62032-10 N/A 65700 N/A X X X X X X 

061184 N/A 65700 N/A X X X X X X 

061184-1 N/A 65700 N/A X X X X X X 

068076 N/A 65700 N/A X X X X X X 

068695 N/A 65700 N/A X X X X X X 

C61453 N/A 65700 NIA X X (1) 

C61453-1 N/A 65700 N/A X X X X X X 

C61453-15 N/A 65700 N/A X X X X X X 

Rack C61453-20 N/A 65700 N/A X X X X X X 

C61453-40 N/A 65700 N/A X X X X X X 

C61453-41 N/A 65700 N/A X X X X X X 

C61453-205 N/A 65700 N/A X X X X X X 
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SAFE LIFE LIMITS (.,.) Affected Model(s) 

Part Name Part Number B2-1A B2K-3C B4-2C C4-203 FH LOG Cal B2-1C B2-20x 82-320 B4-1xx 84-2xx F4-203 

C59050-30 N/A 24000 N/A X X X X X X 

C59050-40 N/A 24000 N/A X X X X X X 

C59050-50 N/A 65700 N/A X X X X X X 

C59050-60 N/A 65700 N/A X X X X X X 

C59050 N/A 24000 N/A X X(1) Turning tube 

C59050-2 N/A 24000 N/A X X(1) X X X X 

C59050-3 NIA 24000 N/A X X(1) 

C59050-4 N/A 24000 N/A X X X X X X 

C59050-20 N/A 24000 N/A X X X X X X 

C59050-28 N/A 24000 N/A X X(1) X X X X 

C62223-1 N/A 65700 N/A X X X X X X 

Torque link pin C62223-15 N/A 65700 N/A X X X X X X (Upper & Lower) 

C62223-20 N/A 65700 N/A X X X X X X 

C59562-2 N/A 65700 N/A X X X X X X 

Torque Links C59562-3 N/A 65700 N/A X X X X 

(Upper & Lower) C59562-4 N/A 65700 N/A X X X X X X 

C59562-20 N/A 65700 N/A X X X X X X 

C62041-1 N/A 65700 N/A X X X X X X 

C62041-15 N/A 65700 N/A X X X X X X 

Torque link C62041-20 N/A 65700 N/A X X X X X X 

medium pin C62041-200 N/A 65700 N/A X X X X X X 

053431 N/A 65700 N/A X X X X X X 

053431-20 N/A 65700 N/A X X X X X X 

SL40110P ~ lA A X X X X 

SHOCK ABSORBER ASSEMBLY 

(1) Limitation applicable to WV01 & WV03 only. 

(2) Limitation applicable to WV 00 only. 

(3) Limitation applicable to WV 08 only. 

(4) Part must be replaced by a new one every time it is removed from the sliding rod. 

(5) Part must be replaced by a new one every time it is removed from the upper rod. 

I C62270 .. ~ ,. TJ X X X X X 

C62034-1 N/A 65700 N/A X X X X X X 

Upper cam C62034-10 NIA 65700 NIA X X X X X X 

C68534 N/A 65700 N/A X X X X X X 
Federal Register / Vol. 83, No. 181 / Tuesday, September 18, 2018 / Rules and Regulations 47053 

BILLING CODE 4910–13–P 

(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 (j)(1) of 

this AD. 

(i) Terminating Action for AD 2014–16–13 

Accomplishing the actions required by this 

AD terminates all requirements of AD 2014– 

16–13. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards Branch, 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 International Section, send it 

to the attention of the person identified in 

paragraph (k)(2) of this AD. Information may 

be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Section, 

Transport Standards Branch, FAA; or the 

European Aviation Safety Agency (EASA); or 

Airbus SAS’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOA– 

authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0145, dated August 31, 2017, for 

related information. This MCAI may be 

found in the AD docket on the internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2018–0390. 

(2) For more information about this AD, 

contact Dan Rodina, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 2200 South 216th St., Des 

Moines, WA 98198; telephone and fax 206– 

231–3225. 

(l) Material Incorporated by Reference 

None. 

Issued in Des Moines, Washington, on 

August 24, 2018. 

James Cashdollar, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–19854 Filed 9–17–18; 8:45 am] 

BILLING CODE 4910–13–P 


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