This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

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new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

37485 

Vol. 81, No. 112 

Friday, June 10, 2016 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8138; Directorate 

Identifier 2014–NM–112–AD; Amendment 

39–18552; AD 2016–12–03] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2011–17– 

10, for all Fokker Services B.V. Model 

F.28 Mark 1000, 2000, 3000, and 4000 

airplanes. AD 2011–17–10 required 

inspecting for a by-pass wire between 

the housing of each in-tank fuel quantity 

indication (FQI) cable plug and the 

cable shield, and corrective actions if 

necessary. AD 2011–17–10 also required 

revising the airplane maintenance 

program. This new AD removes certain 

airplanes from the applicability. This 

new AD applies only to Model F.28 

Mark 1000 airplanes and also requires 

revising the airplane maintenance or 

inspection program by incorporating the 

instructions in revised service 

information. This AD was prompted by 

the issuance of revised service 

information to update the critical design 

configuration control limitations 

(CDCCLs) that address potential ignition 

sources inside fuel tanks. We are issuing 

this AD to prevent potential ignition 

sources inside the fuel tanks, which, in 

combination with flammable fuel 

vapors, could result in fuel tank 

explosions and consequent loss of the 

airplane. 

DATES: This AD becomes effective July 

15, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 15, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of September 16, 2011 (76 FR 

50111, August 12, 2011). 

ADDRESSES: For service information 

identified in this final rule, contact 

Fokker Services B.V., Technical 

Services Dept., P.O. Box 1357, 2130 EL 

Hoofddorp, the Netherlands; telephone 

+31 (0)88–6280–350; fax +31 (0)88– 

6280–111; email technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket Number FAA– 

2015–8138. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket Number FAA– 

2015–8138; 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 Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1137; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2011–17–10, 

Amendment 39–16774 (76 FR 50111, 

August 12, 2011) (‘‘AD 2011–17–10’’). 

AD 2011–17–10 applied to all Model 

F.28 Mark 1000, 2000, 3000, and 4000 

airplanes. The NPRM published in the 

Federal Register on January 4, 2016 (81 

FR 34) (‘‘the NPRM’’). The NPRM was 

prompted by the issuance of revised 

service information to update the 

CDCCLs that address potential ignition 

sources inside fuel tanks. The NPRM 

proposed to retain the requirements of 

AD 2011–17–10, and to require revising 

the airplane maintenance or inspection 

program by incorporating the 

instructions in the revised service 

information. The NPRM also proposed 

to remove certain airplanes from the 

applicability. We are issuing this AD to 

prevent potential ignition sources inside 

the fuel tanks, which, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss 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 Airworthiness 

Directive 2014–0111, dated May 8, 2014 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

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

condition on certain Model F.28 Mark 

1000 airplanes. The MCAI states: 

[T]he FAA published Special Federal 

Aviation Regulation (SFAR) 88 [Amendment 

21–78 (66 FR 23086, May 7, 2001). 

Subsequently, SFAR 88 was amended by: 

Amendment 21–82 (67 FR 57490, September 

10, 2002; corrected at 67 FR 70809, 

November 26, 2002) and Amendment 21–83 

(67 FR 72830, December 9, 2002; corrected at 

68 FR 37735, June 25, 2003, to change ‘‘21– 

82’’ to ‘‘21–83’’)], and the Joint Aviation 

Authorities (JAA) published Interim Policy 

INT/POL/25/12. 

The review conducted by Fokker Services 

on the F28 design, in response to these 

regulations, revealed that on certain 

aeroplanes, an interrupted shield contact 

may exist or develop between the housing of 

an in-tank Fuel Quantity Indication (FQI) 

cable plug and the cable shield of the 

shielded FQI system cables in the main and 

collector fuel tanks, which can, under certain 

conditions, form a spark gap. 

This condition, if not detected and 

corrected, may create an ignition source in 

the fuel tank vapour space, possibly resulting 

in a wing fuel tank explosion and consequent 

loss of the aeroplane. 

To address and correct this unsafe 

condition, Fokker Services published Service 

Bulletin (SB) SBF28–28–053 which provides 

instructions, for early production aeroplanes, 

for a one-time inspection to check for the 

presence of a by-pass wire between the 

housing of each in-tank FQI cable plug and 

the cable shield and, depending on findings, 

for the installation of a by-pass wire. In 

addition, SBF28–28–053 provides a Critical 


asabaliauskas on DSK3SPTVN1PROD with RULES
37486 Federal Register / Vol. 81, No. 112 / Friday, June 10, 2016 / Rules and Regulations 

Design Configuration Control Limitation 

(CDCCL) item to make certain that the bypass wire remains installed on these 

aeroplanes. 

On later production aeroplanes, an 

improved plug Part Number (P/N) 20P227–2 

was introduced with a better shield 

connection to the housing of the plug. 

Therefore, SBF28–28–053 (original issue and 

Revision 1) also provided a CDCCL item to 

ensure that this type of plug remains 

installed on those aeroplanes. 

EASA issued AD 2010–0217 [which 

corresponds to FAA AD 2011–17–10, 

Amendment 39–16774 (76 FR 50111, August 

12, 2011)] to require accomplishment of the 

instructions related to the by-pass wire and 

implementation of the CDCCL items as 

specified in Fokker Services SBF28–28–053 

Revision 1, as applicable to aeroplane s/n. 

Since EASA AD 2010–0217 was issued, it 

was identified that P/N 20P227–1 and 

20P228–1 plugs are also approved and can 

therefore be installed on the later production 

aeroplanes. Prompted by this finding, Fokker 

Services issued SBF28–28–055 to address the 

implementation of a CDCCL item to make 

certain that only approved plug types remain 

installed on the later production aeroplanes, 

while SBF28–28–053 Revision 2 was issued 

for early production aeroplanes to address 

the by-pass wire related actions only. 

Consequently, EASA issued AD 2011– 

0184, retaining the requirements of EASA AD 

2010–0217, which was superseded, to require 

implementation of the related CDCCL items 

as specified in Fokker Services SBF28–28– 

053 Revision 2, or SBF28–28–055, as 

applicable to aeroplane s/n. 

More recently, Fokker Services published 

Revision 3 of SBF28–28–053, to eliminate the 

use of a heat gun in or near to the fuel tank, 

and prompted by a change to the definition 

of the related CDCCL item. Fokker Services 

also cancelled SBF28–28–055, due to the 

introduction of a revised definition of the 

CDCCL item that has been published in 

Fokker Services SBF28–28–050, Revision 2. 

For the reason described above, this 

[EASA] AD retains the requirements related 

to SBF28–28–053 of EASA AD 2011–0184, 

which is superseded, but requires those 

actions to be accomplished in accordance 

with the instructions of Fokker Services 

SBF28–28–053, Revision 3 (R3). 

All the actions related to SBF28–28–055, as 

previously required through paragraphs (5) 

and (6) of EASA AD 2011–0184, are now 

addressed by EASA AD 2014–0110 [http://

ad.easa.europa.eu/ad/2014-0110_1.pdf]. 

* * * * * 

The CDCCL requirement in AD 2011– 

17–10 for Model F.28 Mark 2000, 3000, 

and 4000 airplanes is now addressed in 

other related rulemaking. Therefore, this 

AD does not include Model F.28 Mark 

2000, 3000, and 4000 airplanes in the 

applicability. 

This AD also removes airplanes 

having serial numbers 11993 and 11994 

from the applicability because those 

airplanes were scrapped and removed 

from the type certificate data sheet. 

The unsafe condition is the potential 

of ignition sources inside fuel tanks. 

Such ignition sources, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss of the airplane. You may examine 

the MCAI in the AD docket on the 

Internet at http://www.regulations.gov 

by searching for and locating it in 

Docket No. FAA–2015–8138. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

Fokker Services B.V. has issued 

Fokker Service Bulletin SBF28–28–053, 

Revision 3, dated January 9, 2014. The 

service information describes 

procedures for inspecting for a by-pass 

wire between the housing of each intank FQI cable plug and the cable 

shield, and installing a by-pass wire if 

necessary. The service information also 

describes CDCCL Item 1.7 for fuel 

quantity indicating system (FQIS) 

wiring in wing tanks. 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 5 

airplanes of U.S. registry. This AD adds 

a requirement to revise the airplane 

maintenance or inspection program by 

incorporating the instructions in revised 

service information. The current costs 

associated with this AD are repeated as 

follows for the convenience of affected 

operators: 

The actions required by AD 2011–17– 

10 will take about 6 work-hours per 

product, at an average labor rate of $85 

per work-hour. Required parts cost 

about $0 per product. Based on these 

figures, the estimated cost of the actions 

that were required by AD 2011–17–10 is 

$510 per product. 

In addition, we estimate that any 

necessary follow-on actions required by 

AD 2011–17–10 take about 7 workhours and require parts costing $308, for 

a cost of $903 per product. We have no 

way of determining the number of 

products that may need these actions. 

We also estimate that it takes about 1 

work-hour per product to revise the 

maintenance or inspection program. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD on U.S. operators to be 

$425, or $85 per product. 

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. 

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. 


asabaliauskas on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 81, No. 112 / Friday, June 10, 2016 / Rules and Regulations 37487 

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) 

2011–17–10, Amendment 39–16774 (76 

FR 50111, August 12, 2011), and adding 

the following new AD: 

2016–12–03 Fokker Services B.V.: 

Amendment 39–18552. Docket No. 

FAA–2015–8138; Directorate Identifier 

2014–NM–112–AD. 

(a) Effective Date 

This AD becomes effective July 15, 2016. 

(b) Affected ADs 

This AD replaces AD 2011–17–10, 

Amendment 39–16774 (76 FR 50111, August 

12, 2011) (‘‘AD 2011–17–10’’). 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model F.28 Mark 1000 airplanes; certificated 

in any category; serial numbers (S/Ns) 11003 

through 11041 inclusive, and S/Ns 11991 and 

11992. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by the issuance of 

revised service information to update the 

critical design configuration control 

limitations (CDCCLs) that address potential 

ignition sources inside fuel tanks. We are 

issuing this AD to prevent potential ignition 

sources inside the fuel tanks, which, in 

combination with flammable fuel vapors, 

could result in fuel tank explosions and 

consequent loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection and Installation, 

With Revised Service Information 

This paragraph restates the requirements of 

paragraph (g) of AD 2011–17–10, with 

revised service information. At a scheduled 

opening of the fuel tanks, but not later than 

84 months after September 16, 2011 (the 

effective date of AD 2011–17–10), do a 

general visual inspection for the presence of 

a by-pass wire between the housing of each 

in-tank fuel quantity indication (FQI) cable 

plug and the cable shield, in accordance with 

Part 1 of the Accomplishment Instructions of 

Fokker Service Bulletin SBF28–28–053, 

Revision 1, dated September 20, 2010; or 

Fokker Service Bulletin SBF28–28–053, 

Revision 3, dated January 9, 2014. As of the 

effective date of this AD, only Fokker Service 

Bulletin SBF28–28–053, Revision 3, dated 

January 9, 2014, may be used. 

(h) Retained Corrective Actions, With 

Revised Service Information 

This paragraph restates the requirements of 

paragraph (h) of AD 2011–17–10, with 

revised service information. If during the 

general visual inspection required by 

paragraph (g) of this AD, it is found that a 

by-pass wire is not installed: Before the next 

flight, install the by-pass wire between the 

housing of the in-tank FQI cable plug and the 

cable shield, in accordance with Part 2 of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF28–28–053, Revision 1, 

dated September 20, 2010; or Fokker Service 

Bulletin SBF28–28–053, Revision 3, dated 

January 9, 2014. As of the effective date of 

this AD, only Fokker Service Bulletin 

SBF28–28–053, Revision 3, dated January 9, 

2014, may be used. 

(i) Retained Maintenance Program Revision 

To Add Fuel Airworthiness Limitation, With 

a New Exception 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–17–10, with a new 

exception. Except as required by paragraph 

(k) of this AD, concurrently with the actions 

required by paragraph (g) of this AD, revise 

the airplane maintenance program by 

incorporating CDCCL–1 specified in 

paragraph 1.L.(1)(c) of Fokker Service 

Bulletin SBF28–28–053, Revision 1, dated 

September 20, 2010. 

(j) Retained Requirement for No Alternative 

Actions, Intervals, and/or CDCCLs, With a 

New Exception 

This paragraph restates the requirements of 

paragraph (k) of AD 2011–17–10 with a new 

exception. Except as required by paragraph 

(k) of this AD: After accomplishing the 

revision required by paragraph (i) of this AD, 

no alternative actions (e.g., inspection, 

interval) and/or CDCCLs may be used unless 

the actions, intervals, and/or CDCCLs are 

approved as an alternative methods of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (n)(1) of 

this AD. 

(k) New Maintenance or Inspection Program 

Revision To Add Fuel Airworthiness 

Limitation 

Within 30 days after the effective date of 

this AD: Revise the airplane maintenance or 

inspection program, as applicable, by 

incorporating CDCCL Item 1.7 as specified in 

paragraph 1.L.(1)(c) of Fokker Service 

Bulletin SBF28–28–053, Revision 3, dated 

January 9, 2014. Accomplishing the revision 

required by this paragraph terminates the 

revision required by paragraph (i) of this AD. 

(l) No Alternative CDCCLs 

After the maintenance or inspection 

program has been revised as required by 

paragraph (k) of this AD, no alternative 

CDCCLs may be used unless the CDCCLs are 

approved as an AMOC in accordance with 

the procedures specified in paragraph (n)(1) 

of this AD. 

(m) Credit for Previous Actions 

This paragraph provides credit for the 

applicable actions required by paragraph (k) 

of this AD, if those actions were performed 

before the effective date of this AD using 

Fokker Service Bulletin SBF28–28–053, 

Revision 2, dated June 22, 2011. This 

document is not incorporated by reference in 

this AD. 

(n) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@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: As of the 

effective date of this AD, 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 Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Fokker B.V. Service’s EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0111, dated 

May 8, 2014, 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– 

2015–8138. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (p)(5) and (p)(6) of this AD. 

(p) 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 this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on July 15, 2016. 


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37488 Federal Register / Vol. 81, No. 112 / Friday, June 10, 2016 / Rules and Regulations 

(i) Fokker Service Bulletin SBF28–28–053, 

Revision 3, dated January 9, 2014. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on September 16, 2011 (76 

FR 50111, August 12, 2011). 

(i) Fokker Service Bulletin SBF28–28–053, 

Revision 1, dated September 20, 2010. 

(ii) Reserved. 

(5) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 1357, 

2130 EL Hoofddorp, the Netherlands; 

telephone +31 (0)88–6280–350; fax +31 

(0)88–6280–111; email technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.com. 

(6) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(7) 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 May 31, 

2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–13545 Filed 6–9–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4813; Directorate 

Identifier 2013–NM–161–AD; Amendment 

39–18532; AD 2016–11–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 99–16–01 

for certain 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). AD 99–16– 

01 required repetitive inspections of 

certain bolt holes where parts of the 

main landing gear (MLG) are attached to 

the wing rear spar, and repair if 

necessary. Since we issued AD 99–16– 

01, we have determined that the risk of 

cracking in the wing rear spar is higher 

than initially determined. This new AD 

adds airplanes to the applicability, 

reduces the compliance times and 

repetitive intervals for the inspections, 

and changes the inspection procedures. 

This AD was prompted by a 

determination that the risk of cracking 

in the wing rear spar is higher than 

initially determined. We are issuing this 

AD to detect and correct cracking of the 

rear spar of the wing, which could result 

in reduced structural integrity of the 

airplane. 

DATES: This AD becomes effective July 

15, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 15, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of November 9, 1995 (60 FR 

52618, October 10, 1995). 

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 Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2015–4813. 

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–2015– 

4813; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (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 Branch, ANM–116, 

Transport Airplane Directorate, 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 to supersede AD 99–16–01, 

Amendment 39–11236 (64 FR 40743, 

July 28, 1999) (‘‘AD 99–16–01’’). AD 99– 

16–01 superseded AD 95–20–02, 

Amendment 39–9380 (60 FR 52618, 

October 10, 1995). AD 99–16–01 applied 

to certain 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 

November 17, 2015 (80 FR 71751) (‘‘the 

NPRM’’). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0180, dated August 9, 

2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for certain 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: 

During full-scale fatigue testing, cracks 

were found on the rear spar from certain bolt 

holes at the attachment of the Main Landing 

gear (MLG) forward pick-up fitting and the 

MLG Rib 5 aft. 

This condition, if not detected and 

corrected, could reduce the structural 

integrity of the aeroplane. 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France issued * * * [an AD] (later 

revised) to require High Frequency Eddy 

Current (HFEC) or Ultrasonic (U/S) 

inspections of certain fastener holes where 

the MLG forward pick-up fitting and MLG 

Rib 5 aft are attached to the rear spar. 

Since DGAC France * * * [issued a 

revised AD, which corresponded to FAA AD 

99–16–01, Amendment 39–11236 (64 FR 

40743, July 28, 1999), which superseded 

FAA AD 95–20–02, Amendment 39–9380 (60 

FR 52618, October 10, 1995)] * * *, a fleet 

survey and updated Fatigue and Damage 

Tolerance analyses have been performed in 

order to substantiate the second A300–600 

Extended Service Goal (ESG2) exercise. The 

results of these analyses have shown that the 

threshold and interval must be reduced to 

allow timely detection of these cracks and 

accomplishment of an applicable corrective 

action. 

For the reasons described above, this 

[EASA] AD retains the requirements of [the 

revised DGAC France AD], which is 

superseded, but reduces the related 

compliance times. 

The new, reduced threshold for the 

initial inspection ranges between 8,900 


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