26556 Federal Register / Vol. 83, No. 111 / Friday, June 8, 2018 / Rules and Regulations 

(v) Add together the amounts 

computed in paragraphs (c)(3)(i) 

through (v) of this section and from that 

sum deduct any payment made 

pursuant to paragraph (c)(1) of this 

section. 

(d) Handler underpayment proration. 

If a handler has not received full 

payment from the market administrator 

pursuant to § 1051.72 by the payment 

date specified in paragraph (a), (b), or (c) 

of this section, the handler may reduce 

pro rata its payments to producers or to 

the cooperative association (with 

respect to receipts described in 

paragraph (b) of this section, prorating 

the underpayment to the volume of milk 

received from the cooperative 

association in proportion to the total 

milk received from producers by the 

handler), but not by more than the 

amount of the underpayment. The 

payments shall be completed on the 

next scheduled payment date after 

receipt of the balance due from the 

market administrator. 

(e) Payments to missing or deceased 

producers. If a handler claims that a 

required payment to a producer cannot 

be made because the producer is 

deceased or cannot be located, or 

because the cooperative association or 

its lawful successor or assignee is no 

longer in existence, the payment shall 

be made to the producer-settlement 

fund, and in the event that the handler 

subsequently locates and pays the 

producer or a lawful claimant, or in the 

event that the handler no longer exists 

and a lawful claim is later established, 

the market administrator shall make the 

required payment from the producersettlement fund to the handler or to the 

lawful claimant, as the case may be. 

(f) Producer payment record. In 

making payments to producers pursuant 

to this section, each handler shall 

furnish each producer, except a 

producer whose milk was received from 

a cooperative association handler 

described in § 1000.9(a) or (c), a 

supporting statement in a form that may 

be retained by the recipient which shall 

show: 

(1) The name, address, Grade A 

identifier assigned by a duly constituted 

regulatory agency, and payroll number 

of the producer; 

(2) The daily and total pounds, and 

the month and dates such milk was 

received from that producer; 

(3) The total pounds of butterfat, 

protein, and other solids contained in 

the producer’s milk; 

(4) The minimum rate or rates at 

which payment to the producer is 

required pursuant to the order in this 

part; 

(5) The rate used in making payment 

if the rate is other than the applicable 

minimum rate; 

(6) The amount, or rate per 

hundredweight, or rate per pound of 

component, and the nature of each 

deduction claimed by the handler; and 

(7) The net amount of payment to the 

producer or cooperative association. 

§ 1051.74 [Reserved] 

§ 1051.75 Plant location adjustments for 

producer milk and nonpool milk. 

For purposes of making payments for 

producer milk and nonpool milk, a 

plant location adjustment shall be 

determined by subtracting the Class I 

price specified in § 1051.51 from the 

Class I price at the plant’s location. The 

difference, plus or minus as the case 

may be, shall be used to adjust the 

payments required pursuant to 

§§ 1051.73 and 1000.76. 

§ 1051.76 Payments by a handler 

operating a partially regulated distributing 

plant. 

See § 1000.76. 

§ 1051.77 Adjustment of accounts. 

See § 1000.77. 

§ 1051.78 Charges on overdue accounts. 

See § 1000.78. 

Administrative Assessment and 

Marketing Service Deduction 

§ 1051.85 Assessment for order 

administration. 

On or before the payment receipt date 

specified under § 1051.71, each handler 

shall pay to the market administrator its 

pro rata share of the expense of 

administration of the order at a rate 

specified by the market administrator 

that is no more than 8 cents per 

hundredweight with respect to: 

(a) Receipts of producer milk 

(including the handler’s own 

production) other than such receipts by 

a handler described in § 1000.9(c) that 

were delivered to pool plants of other 

handlers; 

(b) Receipts from a handler described 

in § 1000.9(c); 

(c) Receipts of concentrated fluid milk 

products from unregulated supply 

plants and receipts of nonfluid milk 

products assigned to Class I use 

pursuant to § 1000.43(d) and other 

source milk allocated to Class I pursuant 

to § 1000.44(a)(3) and (8) and the 

corresponding steps of § 1000.44(b), 

except other source milk that is 

excluded from the computations 

pursuant to § 1051.60(h) and (i); and 

(d) Route disposition in the marketing 

area from a partially regulated 

distributing plant that exceeds the skim 

milk and butterfat subtracted pursuant 

to § 1000.76(a)(1)(i) and (ii). 

§ 1051.86 Deduction for marketing 

services. 

See § 1000.86. 

Subpart D—Miscellaneous Provisions 

§ 1051.90 Dates. 

See § 1000.90. 

Dated: June 4, 2018. 

Bruce Summers, 

Administrator, Agricultural Marketing 

Service. 

[FR Doc. 2018–12245 Filed 6–7–18; 8:45 am] 

BILLING CODE 3410–02–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0074; Product 

Identifier 2017–NM–148–AD; Amendment 

39–19309; AD 2018–12–05] 

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 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. This AD was prompted by 

reports of cracks found in the rear spar 

web and lower chord on the left and 

right wings. This AD requires repetitive 

detailed inspections for cracking of the 

rear spar web and lower chord, and 

applicable on-condition actions. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective July 13, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 13, 2018. 

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 service information at the 

FAA, Transport Standards Branch, 2200 

South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 


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Federal Register / Vol. 83, No. 111 / Friday, June 8, 2018 / Rules and Regulations 26557 

It is also available on the internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2018– 

0074. 

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– 

0074; 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 

Docket Operations, 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: 

Payman Soltani, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles 

ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5313; fax: 562–627– 

5210; email: payman.soltani@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 

737–100, –200, –200C, –300, –400, and 

–500 series airplanes. The NPRM 

published in the Federal Register on 

February 9, 2018 (83 FR 5743). The 

NPRM was prompted by reports of 

cracks found in the rear spar web and 

lower chord on the left and right wings. 

The NPRM proposed to require 

repetitive detailed inspections for 

cracking of the rear spar web and lower 

chord, and applicable on-condition 

actions. 

We are issuing this AD to address 

cracks in the rear spar of the left and 

right wing between wing buttock line 

(WBL) 91 and WBL 155, which could 

lead to the inability of a principal 

structural element to sustain required 

flight loads and adversely affect the 

structural integrity of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Support for the NPRM 

The Boeing Company stated its 

support for the NPRM. 

Request To Require the Same Grace 

Period Regardless of Inspection Method 

Southwest Airlines (Southwest), 

requested that we revise paragraph (h) 

of the proposed AD, which refers to the 

‘‘Compliance’’ section of Boeing Alert 

Requirements Bulletin 737–57A1337 

RB, dated September 14, 2017, regarding 

the different compliance times for the 

two inspection methods given in Table 

1 of the ‘‘Compliance’’ section for Group 

2 airplanes. Southwest stated that the 

planned inspection method should have 

no bearing on the timing of the 

inspection, and therefore the 

compliance times should be the same 

for both options. They did not specify 

which of the two compliance times they 

would favor. 

We acknowledge the commenter’s 

request. While the compliance times for 

inspections are not normally dependent 

on the planned inspection method, in 

this case, the initial compliance times 

were adjusted to account for differences 

in the probability of detection using a 

visual inspection versus an eddy current 

inspection. Because an eddy current 

inspection is more capable of detecting 

smaller cracks than a visual inspection, 

the initial compliance time was 

shortened for those airplanes that are 

inspected using the visual inspection 

option. We have not changed this AD in 

this regard. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

the installation of winglets using 

Supplemental Type Certificate (STC) 

ST01219SE does not affect the actions 

specified in the NPRM. 

We agree with the commenter. We 

have redesignated paragraph (c) of the 

proposed AD as paragraph (c)(1) of this 

AD and added paragraph (c)(2) to this 

AD to state that installation of STC 

ST01219SE does not affect the ability to 

accomplish the actions required by this 

AD. Therefore, for airplanes on which 

STC ST01219SE is installed, a ‘‘change 

in product’’ alternative method of 

compliance (AMOC) approval request is 

not necessary to comply with the 

requirements of 14 CFR 39.17. 

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. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert 

Requirements Bulletin 737–57A1337 

RB, dated September 14, 2017. This 

service information describes 

procedures for repetitive detailed or 

surface High Frequency Eddy Current 

(HFEC) inspections for cracking of the 

rear spar web and lower chord, and 

applicable on-condition actions. 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 160 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspections ............. Up to 22 work-hours × $85 per hour = up to $1,870 per 

inspection cycle.

$0 Up to $1,870 per 

inspection cycle.

Up to $299,200 per inspection cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 


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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 

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 

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): 

2018–12–05 The Boeing Company: 

Amendment 39–19309; Docket No. 

FAA–2018–0074; Product Identifier 

2017–NM–148–AD. 

(a) Effective Date 

This AD is effective July 13, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes, 

certificated in any category. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/ebd1cec7b301293

e86257cb30045557a/$FILE/ST01219SE.pdf) 

does not affect the ability to accomplish the 

actions required by this AD. Therefore, for 

airplanes on which STC ST01219SE is 

installed, a ‘‘change in product’’ alternative 

method of compliance (AMOC) approval 

request is not necessary to comply with the 

requirements of 14 CFR 39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

found in the rear spar web and lower chord 

on the left and right wings. We are issuing 

this AD to detect and correct cracks in the 

rear spar of the left and right wing between 

wing buttock line (WBL) 91 and WBL 155, 

which could lead to the inability of a 

principal structural element to sustain 

required flight loads and adversely affect the 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions for Group 1 Airplanes 

For airplanes identified as Group 1 in 

Boeing Alert Requirements Bulletin 737– 

57A1337 RB, dated September 14, 2017: 

Within 120 days after the effective date of 

this AD, inspect the airplane and do all 

applicable corrective actions using a method 

approved in accordance with the procedures 

specified in paragraph (j) of this AD. 

(h) Required Actions for Group 2 Airplanes 

For airplanes identified as Group 2 in 

Boeing Alert Requirements Bulletin 737– 

57A1337 RB, dated September 14, 2017: 

Except as required by paragraph (i) of this 

AD, at the applicable times specified in the 

‘‘Compliance’’ section of Boeing Alert 

Requirements Bulletin 737–57A1337 RB, 

dated September 14, 2017, do all applicable 

actions identified in, and in accordance with, 

the Accomplishment Instructions of Boeing 

Alert Requirements Bulletin 737–57A1337 

RB, dated September 14, 2017. 

Note 1 to paragraph (h) of this AD: 

Guidance for accomplishing the actions 

required by this AD is included in Boeing 

Alert Service Bulletin 737–57A1337, dated 

September 14, 2017, which is referred to in 

Boeing Alert Requirements Bulletin 737– 

57A1337 RB, dated September 14, 2017. 

(i) Exceptions to Service Information 

Specifications 

(1) For purposes of determining 

compliance with the requirements of this AD: 

Where Boeing Alert Requirements Bulletin 

737–57A1337 RB, dated September 14, 2017, 

uses the phrase ‘‘the original issue date of 

Requirements Bulletin 737–57A1337 RB,’’ 

this AD requires using ‘‘the effective date of 

this AD.’’ 

(2) Where Boeing Alert Requirements 

Bulletin 737–57A1337 RB, dated September 

14, 2017, specifies contacting Boeing, this AD 

requires repair using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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. Information may be emailed to: 9- 

ANM-LAACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO Branch, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(k) Related Information 

(1) For more information about this AD, 

contact Payman Soltani, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 


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5313; fax: 562–627–5210; email: 

payman.soltani@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (l)(3) and (l)(4) of this AD. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Alert Requirements Bulletin 

737–57A1337 RB, dated September 14, 2017. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

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

MC 110–SK57, Seal Beach, CA 90740–5600; 

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

www.myboeingfleet.com. 

(4) You may view this service information 

at the FAA, Transport Standards Branch, 

2200 South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

(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 Des Moines, Washington, on May 

31, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–12279 Filed 6–7–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–1020; Product 

Identifier 2017–NM–114–AD; Amendment 

39–19306; AD 2018–12–02] 

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 A318–111 and –112 

airplanes; Model A319–111, –112, –113, 

–114, and –115 airplanes; Model A320– 

211, –212, –214, and –216 airplanes; 

and Model A321–111, –112, –211, –212, 

and –213 airplanes. This AD was 

prompted by a review of maintenance 

instructions for a blend repair of the 

snout diameter of the main beam 

assembly of the forward engine mount 

that would create an excessive gap 

between the bearing mono-ball and the 

snout. This AD requires modifying the 

main beam assembly of the forward 

engine mount. We are issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective July 13, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 13, 2018. 

ADDRESSES: For Airbus service 

information identified in this final rule, 

contact Airbus, Airworthiness Office– 

EIAS, 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.airwortheas@airbus.com; internet: http://

www.airbus.com. For Goodrich service 

information identified in this final rule, 

contact Goodrich Corporation, 

Aerostructures, 850 Lagoon Drive, Chula 

Vista, CA 91910–2098; phone: 619–691– 

2719; email: jan.lewis@goodrich.com; 

internet: http://www.goodrich.com/ 

TechPubs. You may view this 

referenced service information at the 

FAA, Transport Standards Branch, 2200 

South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

It is also available on the internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2017– 

1020. 

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– 

1020; 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198–6547; 

telephone 425–227–1405; 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 A318–111 

and –112 airplanes; Model A319–111, 

–112, –113, –114, and –115 airplanes; 

Model A320–211, –212, –214, and –216 

airplanes; and Model A321–111, –112, 

–211, –212, and –213 airplanes. The 

NPRM published in the Federal 

Register on October 24, 2017 (82 FR 

49146) (‘‘the NPRM’’). The NPRM was 

prompted by a review of maintenance 

instructions for a blend repair of the 

snout diameter of the main beam 

assembly of the forward engine mount 

that would create an excessive gap 

between the bearing mono-ball and the 

snout. The NPRM proposed to require 

modifying the main beam assembly of 

the forward engine mount. We are 

issuing this AD to prevent in-flight 

failure of a forward engine mount, and 

consequent detachment of an engine, 

which could result in reduced 

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– 

0132R1, dated November 22, 2017 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for all Airbus Model A318– 

111 and –112 airplanes; Model A319– 

111, –112, –113, –114, and –115 

airplanes; Model A320–211, –212, –214, 

and –216 airplanes; and Model A321– 

111, –112, –211, –212, and –213 

airplanes. The MCAI states: 

A review of maintenance instructions 

revealed that the Goodrich Aerospace 

CFM56–5B, Forward Engine Mount 

Component Maintenance Manual (CMM) 71– 

21–08, revision (rev.) 1 up to 46 (inclusive), 

repair 10 (Blend Repair-Beam Assembly 

Snout Diameter), provides instructions to 

blend the wear on the forward engine mount 

assembly, Part Number (P/N) 642–2000–9, 

642–2000–13, or 642–2000–25, creating an 

excessive gap between the bearing mono-ball 

and the snout of the forward engine mount 

main beam assembly, P/N 642–2006–501, or 

P/N 642–2006–503. 

This condition, if not detected and 

corrected, could lead to in-flight failure of a 

forward engine mount and consequent 

detachment of an engine, possibly resulting 

in reduced control of the aeroplane and 

injury to persons on the ground. 

To address this potential unsafe condition, 

Airbus issued Service Bulletin (SB) A320– 

71–1065 and SB A320–71–1066, and 


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