1532 Federal Register / Vol. 83, No. 9 / Friday, January 12, 2018 / Rules and Regulations 

(ii) Part II of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, Revision 1, dated May 25, 

1995. 

(iii) Part II of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, dated June 30, 1994. 

(4) Airplanes on which the outboard chord 

has not been replaced in accordance with the 

method specified in paragraph (h)(4)(i), 

(h)(4)(ii), or (h)(4)(iii) of this AD. 

(i) Part 3 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, Revision 2, dated May 25, 

2006. 

(ii) Part I of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, Revision 1, dated May 25, 

1995. 

(iii) Part I of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, dated June 30, 1994. 

(i) Edge Margin Measurement, Related 

Investigative Actions, and Repair 

For Model 737–100, –200, and –200C 

series airplanes having line numbers 1 

through 999 inclusive, identified as Groups 

1 through 3 in Boeing Alert Service Bulletin 

737–53A1166, Revision 2, dated May 25, 

2006, on which the preventive modification 

has been installed in accordance with Boeing 

Alert Service Bulletin 737–53A1166, dated 

June 30, 1994; or Boeing Alert Service 

Bulletin 737–53A1166, Revision 1, dated 

May 25, 1995: Within 60,000 flight cycles 

after accomplishing the preventive 

modification, determine if the modification is 

classified as interim or permanent by using 

the edge margin measurement classification 

specified in part 6 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, Revision 2, dated May 25, 

2006. In lieu of measuring on the airplane, 

a review of engineering documentation may 

be used to classify the modification if the 

engineering documentation was completed at 

the time of the modification and has the edge 

margins recorded. 

(1) If the modification is classified as 

permanent, no further action is required by 

paragraph (i) of this AD. 

(2) If the modification is classified as 

interim: Within 60,000 flight cycles after 

accomplishment of the interim modification 

of the outboard chord of the frame at BS 727 

at S–18A, but no earlier than 50,000 flight 

cycles after accomplishment of the 

modification, do a one-time follow-on openhole eddy current inspection to detect cracks 

in the modified chord, in accordance with 

part 8 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1166, 

Revision 2, dated May 25, 2006. If any crack 

is found, before further flight, repair in 

accordance with part 3 or part 4, as 

applicable, of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, Revision 2, dated May 25, 

2006; except, if the repairs cannot be 

installed using the identified procedures, 

repair before further flight using a method 

approved in accordance with the procedures 

specified in paragraph (l) of this AD. 

(j) Follow-On Inspection for Interim 

Modification and Repair 

For airplanes having line numbers 1 

through 3132 inclusive, on which an interim 

modification of the BS 727 outboard chord as 

defined in part 6 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, Revision 2, dated May 25, 

2006, has been accomplished: Within 60,000 

flight cycles after accomplishment of the 

interim modification of the outboard chord of 

the frame at BS 727 at S–18A, but no earlier 

than 50,000 flight cycles after 

accomplishment of the modification, do a 

one-time follow-on open-hole eddy current 

inspection to detect cracks in the modified 

chord, in accordance with part 8 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1166, Revision 2, 

dated May 25, 2006. If any crack is found 

during the inspection required by this 

paragraph, before further flight, repair in 

accordance with part 3 or part 4, as 

applicable, of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, Revision 2, dated May 25, 

2006; except, where the repairs cannot be 

installed using the procedures identified in 

this service bulletin, repair before further 

flight using a method approved in 

accordance with the procedures specified in 

paragraph (l) of this AD. 

(k) Exception to the Service Information 

Access and restoration procedures 

specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1166, Revision 2, dated May 25, 

2006, are not required by this AD. Operators 

may do those actions following their 

approved maintenance procedures. 

(l) 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 (m) of this 

AD. Information may be emailed to: 9-ANMLAACO-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. 

(m) Related Information 

For more information about this AD, 

contact George Garrido, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

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

5232; fax: 562–627–5210; email: 

george.garrido@faa.gov. 

(n) 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. 

(3) The following service information was 

approved for IBR on December 26, 2012 (77 

FR 69747, November 21, 2012). 

(i) Boeing Alert Service Bulletin 737– 

53A1166, Revision 2, dated May 25, 2006. 

(ii) Reserved. 

(4) 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; 

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

www.myboeingfleet.com. 

(5) You may view this 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. 

(6) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on January 

2, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–00256 Filed 1–11–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–1242; Product 

Identifier 2013–NM–043–AD; Amendment 

39–19150; AD 2018–01–09] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 95–25–02, 

which applied to certain Fokker 

Services B.V. Model F28 Mark 0100 


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Federal Register / Vol. 83, No. 9 / Friday, January 12, 2018 / Rules and Regulations 1533 

airplanes. AD 95–25–02 required 

inspection(s) to detect cracks of the 

fuselage-mounted half of hinge 

assemblies of the small cargo door, and 

replacement of any cracked hinge 

assembly with a new hinge assembly. 

This new AD was prompted by a report 

that the hinges of the small cargo door 

are made of a material that is sensitive 

to stress corrosion and fatigue cracking, 

and by the determination that the 

existing inspection program does not 

provide sufficient protection against 

fatigue-induced cracks. This AD 

requires contacting the FAA to obtain 

instructions for addressing the unsafe 

condition on these products, and doing 

the actions specified in those 

instructions. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD becomes effective 

January 29, 2018. 

We must receive comments on this 

AD by February 26, 2018. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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– 

1242; or in person at the Docket 

Operations office 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 Operations office (telephone: 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 1601 Lind 

Avenue SW, Renton, WA 98057–3356; 

telephone: 425–227–1137; fax: 425– 

227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued AD 95–25–02, Amendment 

39–9446 (60 FR 63615, December 12, 

1995) (‘‘AD 95–25–02’’), which applied 

to certain Fokker Services B.V. Model 

F28 Mark 0100 airplanes. AD 95–25–02 

was prompted by a report that the 

hinges of the small cargo door are made 

of a material that is sensitive to stress 

corrosion cracking. AD 95–25–02 

required inspection(s) to detect cracks of 

the fuselage-mounted half of hinge 

assemblies of the small cargo door, and 

replacement of any cracked hinge 

assembly with a new hinge assembly. 

We issued AD 95–25–02 to prevent 

failure of the hinges of the small cargo 

door due to stress corrosion cracking, 

which could result in opening and/or 

separation of the door while the 

airplane is in flight, and resultant rapid 

decompression and/or structural 

damage to the airplane. 

Since we issued AD 95–25–02, we 

have determined that the existing 

inspection program does not provide 

sufficient protection against fatigueinduced cracks. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2013–0028, 

dated February 8, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Fokker Services B.V. Model 

F28 Mark 0100 airplanes. The MCAI 

states: 

Over the years, stress corrosion- and 

fatigue-induced cracks were found on the 

hinges of the downward opening small cargo 

doors installed on Fokker F28 Mark 0100 

aeroplanes. 

To address the potential unsafe condition 

with respect to stress corrosion, CAA–NL 

issued AD (BLA) 93–036/2 [which 

corresponded to FAA AD 95–25–02] to 

require repetitive inspections and, if cracks 

are found, replacement of the hinges with 

hinges of a new design. These new hinges 

were installed before delivery on aeroplanes 

with s/n 11409 and higher. 

To ensure the continued structural 

integrity with respect to fatigue, a repetitive 

inspection was included in the 

Airworthiness Limitations Section (ALS) of 

the Instructions for Continued Airworthiness. 

As part of the Widespread Fatigue Damage 

re-evaluation, it was concluded that the 

repetitive fatigue inspection in the ALS does 

not provide a sufficient level of protection 

against the fatigue-induced cracks. 

For the reasons described above, this 

[EASA] AD retains the requirements of CAA– 

NL AD 93–036/2, which is superseded, and 

requires replacement of Part Number (P/N) 

A28410–405 and P/N A28410–407 hinges 

with modified P/N D28410–409 hinges. 

You may examine the MCAI on the 

internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2017–1242. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI. We are issuing this AD because 

we evaluated all pertinent information 

and determined the unsafe condition 

exists and is likely to exist or develop 

on other products of the same type 

design. 

FAA’s Determination of the Effective 

Date 

Since there are currently no domestic 

operators of this product, we find good 

cause that notice and opportunity for 

prior public comment are unnecessary. 

In addition, for the reason(s) stated 

above, we find that good cause exists for 

making this amendment effective in less 

than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2017–1242; 

Product Identifier 2013–NM–043–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD based on those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

Currently, there are no affected U.S.- 

registered airplanes. This AD requires 

contacting the FAA to obtain 

instructions for addressing the unsafe 

condition, and doing the actions 

specified in those instructions. Based on 

the actions specified in the MCAI AD, 


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1534 Federal Register / Vol. 83, No. 9 / Friday, January 12, 2018 / Rules and Regulations 

we are providing the following cost estimates for an affected airplane that is 

placed on the U.S. Register in the future: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product 

Inspections (retained actions from AD 95–25– 

02).

2 work-hours × $85 per hour = $170 per inspection cycle.$0 ............................... $170 per inspection 

cycle. 

Replacement (new action) ............................... Up to 186 work-hours × $85 per hour = 

$15,810.

Up to $7,700 .............. Up to $23,510. 

We estimate the following costs to do 

any necessary on-condition 

replacements that would be required 

based on the results of the required 

actions: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Replacement (retained actions from AD 95– 

25–02).

Up to 186 work-hours × $85 per hour = 

$15,810.

Up to $7,700 .............. Up to $23,510. 

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 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to transport category 

airplanes to the Director of the System 

Oversight Division. 

Regulatory Findings 

We 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 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 

removing airworthiness directive (AD) 

95–25–02, Amendment 39–9446 (60 FR 

63617, December 12, 1995), and adding 

the following new AD: 

2018–01–09 Fokker Services B.V.: 

Amendment 39–19150; Docket No. 

FAA–2017–1242; Product Identifier 

2013–NM–043–AD. 

(a) Effective Date 

This AD becomes effective January 29, 

2018. 

(b) Affected ADs 

This AD replaces AD 95–25–02, 

Amendment 39–9446 (60 FR 63615, 

December 12, 1995) (‘‘AD 95–25–02’’). 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model F28 Mark 0100 series airplanes, 

certificated in any category, serial numbers 

11244 through 11267 inclusive, 11284, 

11285, 11287, 11288, 11290, 11292, 11294, 

11296, 11298, 11299, 11301, 11302, 11304, 

11305, 11307, 11309, 11311, 11315, 11317, 

11319, 11320, 11322, 11336, 11339, 11341 

through 11344 inclusive, 11347, 11348, 

11350, 11351, 11362 through 11364 

inclusive, 11371, 11374, 11375, 11381 

through 11384 inclusive, 11386, 11389, 

11390, 11394, and 11401. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 52, Doors. 

(e) Reason 

This AD was prompted by a report that the 

hinges of the small cargo door are made of 

a material that is sensitive to stress corrosion 

cracking, and by the determination that the 

existing inspection program does not provide 

sufficient protection against fatigue-induced 

cracks. We are issuing this AD to prevent 

failure of the hinges of the small cargo door 

due to stress corrosion cracking, which could 

result in opening and/or separation of the 

door while the airplane is in flight, and 

resultant rapid decompression and/or 

structural damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 


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Federal Register / Vol. 83, No. 9 / Friday, January 12, 2018 / Rules and Regulations 1535 

(g) Required Action(s) 

Within 30 days after the effective date of 

this AD, request instructions from the 

Manager, International Section, Transport 

Standards Branch, FAA, to address the 

unsafe condition specified in paragraph (e) of 

this AD; and accomplish the action(s) at the 

times specified in, and in accordance with, 

those instructions. Guidance can be found in 

Mandatory Continuing Airworthiness 

Information (MCAI) European Aviation 

Safety Agency (EASA) AD 2013–0028, dated 

February 8, 2013. 

(h) 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 (i)(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. 

(i) Related Information 

(1) Refer to MCAI EASA AD 2013–0028, 

dated February 8, 2013, for related 

information. You may examine the MCAI on 

the internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2017–1242. 

(2) For more information about this AD, 

contact Tom Rodriguez, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 1601 Lind Avenue SW, 

Renton, WA 98057–3356; telephone: 425– 

227–1137; fax: 425–227–1149. 

(j) Material Incorporated by Reference 

None. 

Issued in Renton, Washington, on January 

2, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–00339 Filed 1–11–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–1243; Product 

Identifier 2012–NM–150–AD; Amendment 

39–19151; AD 2018–01–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2011–14– 

10, which applied to certain Airbus 

Model A330–342 airplanes. AD 2011– 

14–10 required repetitive ultrasonic 

inspections for cracks of a certain 

fuselage frame at the fastener hole area 

just above a certain stringer, and repair, 

if necessary. This new AD was 

prompted by a new fatigue and damage 

tolerance evaluation, which showed that 

certain inspection thresholds and 

intervals need to be shorter. This AD 

requires contacting the FAA to obtain 

instructions for addressing the unsafe 

condition on these products, and doing 

the actions specified in those 

instructions. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD becomes effective 

January 29, 2018. 

We must receive comments on this 

AD by February 26, 2018. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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– 

1243; or in person at the Docket 

Operations office 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 Operations office (telephone: 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 1601 Lind 

Avenue SW, Renton, WA 98057–3356; 

telephone: 425–227–1138; fax: 425– 

227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued AD 2011–14–10, 

Amendment 39–16745 (76 FR 41657, 

July 15, 2011) (‘‘AD 2011–14–10’’), 

which applied to certain Airbus Model 

A330–342 airplanes. AD 2011–14–10 

was prompted by a determination that 

airworthiness limitation item (ALI) task 

533105–10–02 was not performed on 

certain airplanes. AD 2011–14–10 

required repetitive ultrasonic 

inspections for cracks of fuselage frame 

39.1 at the fastener hole area just above 

stringer 28, and repair, if necessary. We 

issued AD 2011–14–10 to detect and 

correct fatigue cracking of the internal 

structure of the fuselage, which could 

adversely affect the structural integrity 

of the airplane. 

Since we issued AD 2011–14–10, we 

have determined, based on a new 

fatigue and damage tolerance evaluation 

that took into account airplane usage, 

that the compliance time threshold and 

intervals need to be shorter. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2012–0140, 

dated July 27, 2012 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A330–342 

airplanes. The MCAI states: 

Airworthiness Limitation Item (ALI) task 

533105–01–02 is applicable to aeroplanes on 

which Airbus modification 40391 has not 

been embodied in production. The 

requirements associated to this task are 

applicable to aeroplanes on which 

Modification Proposal (MP) S10374 has not 

been embodied. 

Following a query from an operator, 

investigations revealed that some aeroplane 

[manufacturer serial numbers] MSN, for 

which Airbus modification 40391 was 

indicated as fully embodied inside the 

Aircraft Inspection Report (AIR), did not 


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