63370 Federal Register / Vol. 81, No. 179 / Thursday, September 15, 2016 / Rules and Regulations 

(j) Modification of Overhead Stowage 

Compartments and Re-Identification of Part 

Number 

Within 4 months after the effective date of 

this AD: Modify the overhead stowage 

compartments, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraphs (j)(1) through (j)(4) of this AD. 

(1) For airplanes identified in ATR Service 

Bulletin ATR42–25–0185, dated November 

21, 2014: ATR Service Bulletin ATR42–25– 

0185, dated November 21, 2014. 

(2) For airplanes identified in ATR Service 

Bulletin ATR42–25–0186, dated November 

21, 2014: ATR Service Bulletin ATR42–25– 

0186, dated November 21, 2014. 

(3) For airplanes identified in ATR Service 

Bulletin ATR72–25–1148, dated November 

21, 2014: ATR Service Bulletin ATR72–25– 

1148, dated November 21, 2014. 

(4) For airplanes identified in ATR Service 

Bulletin ATR72–25–1149, dated November 

21, 2014: ATR Service Bulletin ATR72–25– 

1149, dated November 21, 2014. 

(k) 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: 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 

EASA; or ATR—GIE Avions de Transport 

Re ́gional’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(l) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0018, dated 

February 5, 2015, 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–2015–0077. 

(m) 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. 

(i) ATR Service Bulletin ATR42–25–0180, 

dated August 19, 2013. 

(ii) ATR Service Bulletin ATR42–25–0185, 

dated November 21, 2014. 

(iii) ATR Service Bulletin ATR42–25–0186, 

dated November 21, 2014. 

(iv) ATR Service Bulletin ATR72–25–1141, 

dated August 19, 2013. 

(v) ATR Service Bulletin ATR72–25–1148, 

dated November 21, 2014. 

(vi) ATR Service Bulletin ATR72–25–1149, 

dated November 21, 2014. 

(3) For service information identified in 

this AD, contact ATR—GIE Avions de 

Transport Re ́gional, 1, Alle ́e Pierre Nadot, 

31712 Blagnac Cedex, France; telephone +33 

(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; 

email continued.airworthiness@atr.fr; 

Internet http://www.aerochain.com. 

(4) 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. 

(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 Renton, Washington, on August 

25, 2016. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–21292 Filed 9–14–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–6550; Directorate 

Identifier 2013–NM–162–AD; Amendment 

39–18638; AD 2016–18–08] 

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) 90–11–05 

for certain Airbus Model A300 B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and 

B4–203 airplanes and Model A300 B4– 

600 series airplanes. AD 90–11–05 

required repetitive detailed inspections 

for cracking in the aft hinge brackets of 

the outer shroud box that is located in 

the outer wing box, and related 

investigative and corrective actions if 

necessary. This new AD changes certain 

compliance times and adds airplanes to 

the applicability. This AD was 

prompted by reports of cracks in the aft 

hinge brackets of the outer shroud box 

that is located in the outer wing box, 

which were found during routine 

maintenance checks, and our 

subsequent determination that a change 

in inspection compliance times is 

needed. We are issuing this AD to detect 

and correct cracking of the aft hinge 

brackets of the outer shroud box; such 

cracking could affect the structural 

integrity of the airplane. 

DATES: This AD becomes effective 

October 20, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 20, 2016. 

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–2015–6550. 

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– 

6550; 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 


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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 90–11–05, 

Amendment 39–6603 (89–NM–223–AD) 

(55 FR 20129, May 15, 1990) (‘‘AD 90– 

11–05’’). AD 90–11–05 applied to 

certain Airbus Model A300 B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and 

B4 203 airplanes and Model A300 B4– 

600 series airplanes. The NPRM 

published in the Federal Register on 

December 14, 2015 (80 FR 77279) (‘‘the 

NPRM’’). The NPRM was prompted by 

a determination that a change to certain 

compliance times is needed. The NPRM 

proposed to continue to require doing 

repetitive detailed inspections for 

cracking in the hinge brackets of the 

forward and aft outer shroud boxes that 

are located in the outer wing box, and 

related investigative and corrective 

actions if necessary. The NPRM also 

proposed to change certain compliance 

times and add airplanes to the 

applicability. We are issuing this AD to 

detect and correct cracking of the aft 

hinge brackets of the outer shroud box; 

such cracking could affect the structural 

integrity 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 2013–0181R1, dated August 

20, 2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Model 

A300 series airplanes and Model A300 

B4–600 series airplanes. The MCAI 

states: 

In the past, aft hinge brackets of the outer 

wing box were found cracked. Fracture of a 

bracket would allow vertical movement of 

the inner shroud box structure, which could 

result in damage to the top skin of the 

inboard flap. In addition, the loads carried by 

the brackets will be transferred to the 

remaining supports, which may also crack 

and cause extensive structural damage. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To address this potential unsafe condition, 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France issued * * * [an airworthiness 

directive] (later revised) to require repetitive 

inspections of the hinge bracket of the outer 

box and, depending on findings, corrective 

action(s). 

Since that [DGAC] AD was issued, a fleet 

survey and updated Fatigue and Damage 

Tolerance analysis were performed in order 

to substantiate the A300 Extended Service 

Goal (ESG) and A300–600 Extended Service 

Goal (ESG2) exercise. 

The results of these analyses led to a 

change in the inspection thresholds and 

intervals in Flight Cycles (FC) and the 

introduction of Flight Hours (FH) limits. 

For the reasons described above, this 

[EASA] AD retains the requirements of DGAC 

France * * * [an airworthiness directive], 

which is superseded, but requires those 

actions within the new thresholds and 

intervals given by Airbus Service Bulletin 

(SB) A300–57–0142 Revision 04 or A300–57– 

6010 Revision 05, as applicable to aeroplane 

model. 

Revision 1 of this [EASA] AD is issued to 

add model A300 B4–203 aeroplanes to the 

applicability and compliance time tables. 

This model is covered by Airbus SB A300– 

57–0142, but was mistakenly omitted from 

the original [EASA] AD issue. 

The corrective action for a hinge 

bracket that is cracked or fractured is 

replacing the damaged hinge bracket 

with a new bracket. 

For airplanes on which a crack is 

found in one half bracket or both half 

brackets, related investigative actions 

include a general visual inspection for 

secondary damage (e.g., cracks, wear 

damage, pitting, and gouging) in the 

following areas: 

• The inner shroud-box forward 

attachments and the attachment 

brackets at the inboard end. 

• The inner and outer shroud-box 

structure, adjacent to the fractured 

bracket. 

• The top skin of the inboard flap. 

The corrective action for damage 

findings during the related investigative 

action is repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or EASA; or Airbus’s 

EASA Design Organization Approval 

(DOA). 

The compliance time for related 

investigative actions and corrective 

actions is before further flight. 

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–2015– 

6550. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM and the FAA’s 

response to the comment. 

Request To Exclude Certain Airplanes 

From the Applicability 

FedEx requested that we exclude from 

the proposed applicability airplanes on 

which the actions specified in Airbus 

Service Bulletin A300–57–6011, 

Revision 2, dated July 10, 1989, have 

been accomplished. FedEx stated that it 

has accomplished the optional 

terminating actions provided in 

paragraph (j)(1) of the proposed AD, and 

specified in Airbus Service Bulletin 

A300–57–6011, Revision 2, dated July 

10, 1989, on several of its airplanes. 

We disagree with FedEx’s request. As 

of the effective date of this AD, 

additional actions are required for 

airplanes on which the optional 

modification has been accomplished. 

These airplanes will need to have a onetime detailed visual inspection of the 

forward and aft outer shroud box with 

no cracking found, as required by 

paragraph (j)(2) of this AD. We have not 

changed this AD in this regard. 

Changes Made to This AD 

In paragraph (j)(2) of the proposed 

AD, we proposed to provide an optional 

method of compliance (i.e., a 

replacement and a one-time inspection) 

for actions specified in paragraph (g) of 

the proposed AD. We also proposed to 

give credit in paragraph (k)(2) of the 

proposed AD for replacements 

accomplished before the effective date 

of this AD using the same service 

information identified in paragraph 

(j)(2) of the AD: 

• Airbus Service Bulletin A300–57– 

143, dated December 17, 1986. 

• Airbus Service Bulletin A300–57– 

143, Revision 1, dated March 19, 1987. 

• Airbus Service Bulletin A300–57– 

6011, dated December 17, 1986. 

• Airbus Service Bulletin A300–57– 

6011, Revision 1, dated March 19, 1987. 

Since we cannot make this service 

information reasonably available, we 

have revised paragraph (j)(2) of the 

proposed AD, removed redundant 

paragraph (k)(2) of the proposed AD 

from this AD, and redesignated 

paragraph (k)(1) and subsequent 

subparagraphs accordingly. We revised 

paragraph (j)(2) of this AD by removing 

the references to the service information 

and instead specified that operators 

must do the replacement using a 

method approved by the Manager, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA Design 

Organization Approval (DOA). 

Conclusion 

We reviewed the available data, 

including the comment received, 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 


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• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. 

• Airbus Service Bulletin A300–57– 

0142, Revision 04, dated March 30, 

2011, which describes procedures for 

doing an inspection of the forward and 

aft hinge brackets on the outer shroud 

box. 

• Airbus Service Bulletin A300–57– 

143, Revision 2, dated July 10, 1989, 

which describes procedures for 

replacing the aft aluminum alloy 

brackets on the outer shroud box with 

new steel brackets. 

• Airbus Service Bulletin A300–57– 

6010, Revision 05, dated February 21, 

2011, which describes procedures for 

doing an inspection of the forward and 

aft hinge brackets on the outer shroud 

box. 

• Airbus Service Bulletin A300–57– 

6011, Revision 2, dated July 10, 1989, 

which describes procedures for 

replacing the aft aluminum alloy 

brackets on the outer shroud box with 

new steel brackets. 

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 3 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

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

Inspection ...................... 8 work-hours × $85 per hour = $680 per inspection cycle.$0 $680 per inspection 

cycle.

$2,040 per inspection 

cycle. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement .................................... 27 work-hours × $85 per hour = $2,295 ................................................... $25,650 $27,945 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition related 

investigative and corrective actions 

specified in this AD. 

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. 

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) 

90–11–05, Amendment 39–6603 (89– 

NM–223–AD) (55 FR 20129, May 15, 

1990), and adding the following new 

AD: 

2016–18–08 Airbus: Amendment 39–18638. 

Docket No. FAA–2015–6550; Directorate 

Identifier 2013–NM–162–AD. 

(a) Effective Date 

This AD becomes effective October 20, 

2016. 

(b) Affected ADs 

This AD replaces AD 90–11–05, 

Amendment 39–6603 (89–NM–223–AD) (55 

FR 20129, May 15, 1990). 

(c) Applicability 

This AD applies to Airbus Model A300 B2– 

1C, B2K–3C, B2–203, B4–2C, B4–103, and 

B4–203 airplanes; Model A300 B4–601, B4– 

603, B4–620, and B4–622 airplanes; and 

Model A300 B4–605R airplanes; certificated 

in any category; except airplanes on which 

Airbus Modification 6661 has been embodied 

during production. 


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(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports of cracks 

in the aft hinge brackets of the outer shroud 

box that is located in the outer wing box, 

which were found during routine 

maintenance checks, and our subsequent 

determination that a change in inspection 

compliance times is needed. We are issuing 

this AD to detect and correct cracking of the 

aft hinge brackets of the outer shroud box; 

such cracking could affect the structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

At the applicable compliance time 

specified in paragraph (g)(1), (g)(2), or (g)(3) 

of this AD: Do a detailed inspection for 

cracks and fractures of the hinge brackets of 

the forward and aft outer shroud boxes, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–0142, Revision 04, dated March 30, 2011; 

or Airbus Service Bulletin A300–57–6010, 

Revision 05, dated February 21, 2011; as 

applicable. Repeat the inspection thereafter 

at the applicable interval specified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–0142, Revision 04, dated March 30, 2011; 

or Airbus Service Bulletin A300–57–6010, 

Revision 05, dated February 21, 2011; as 

applicable. Doing the replacement specified 

in paragraph (j) of this AD terminates the 

repetitive inspections required by this 

paragraph. 

(1) For Model A300 B4–601, B4–603, B4– 

605R, B4–620, B4–622, B4–2C, and B4–203 

airplanes: Do the inspection at the later of the 

times specified in paragraphs (g)(1)(i) and 

(g)(1)(ii) of this AD. Repeat the inspection 

thereafter at intervals not to exceed 1,000 

flight cycles or 2,000 flight hours, whichever 

occurs first. 

(i) Before the accumulation of 5,000 flight 

cycles or 10,400 flight hours since first flight, 

whichever occurs first. 

(ii) Within 100 flight cycles after the 

effective date of this AD. 

(2) For Model A300 B2–1C, B2–203, and 

B2K–3C airplanes: Do the inspection at the 

later of the times specified in paragraphs 

(g)(2)(i) and (g)(2)(ii) of this AD. Repeat the 

inspection thereafter at intervals not to 

exceed 1,000 flight cycles or 1,000 flight 

hours, whichever occurs first. 

(i) Before the accumulation of 5,000 flight 

cycles or 5,400 flight hours since first flight, 

whichever occurs first. 

(ii) Within 100 flight cycles after the 

effective date of this AD. 

(3) For Model A300 B4–103 airplanes: Do 

the inspection at the later of the times 

specified in paragraphs (g)(3)(i) and (g)(3)(ii) 

of this AD. Repeat the inspection thereafter 

at intervals not to exceed 1,000 flight cycles 

or 1,300 flight hours, whichever occurs first. 

(i) Before the accumulation of 5,000 flight 

cycles or 6,600 flight hours since first flight, 

whichever occurs first. 

(ii) Within 100 flight cycles after the 

effective date of this AD. 

(h) Corrective Action 

If any crack or fracture is found during any 

inspection required by paragraph (g) of this 

AD: Before further flight, replace the 

damaged hinge bracket with a new bracket, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–143, Revision 2, dated July 10, 1989; or 

Airbus A300–57–6011, Revision 2, dated July 

10, 1989; as applicable. 

(i) Related Investigative and Corrective 

Actions 

If any crack or fracture is found during any 

inspection required by paragraph (g) of this 

AD: Before further flight, do a general visual 

inspection for secondary damage (e.g., cracks, 

wear damage, pitting, and gouging) in the 

areas specified in paragraphs (i)(1), (i)(2), and 

(i)(3) of this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–0142, Revision 04, 

dated March 30, 2011; or Airbus Service 

Bulletin A300–57–6010, Revision 05, dated 

February 21, 2011; as applicable. If any 

damage is found, before further flight, repair 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA). 

(1) The inner shroud-box forward 

attachments and the attachment brackets at 

the inboard end. 

(2) The inner and outer shroud-box 

structure, adjacent to the fractured bracket. 

(3) The top skin of the inboard flap. 

(j) Optional Terminating Action for 

Inspection Requirements of Paragraph (g) of 

This AD 

(1) Replacement of the hinge bracket, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–143, Revision 2, dated July 10, 1989 (for 

Model A300 series airplanes); or Airbus 

Service Bulletin A300–57–6011, Revision 2, 

dated July 10, 1989; as applicable; terminates 

the inspection requirements of paragraph (g) 

of this AD (for Model A300 B4–600 series 

airplanes). 

(2) Replacement of a hinge bracket before 

the effective date of this AD terminates the 

repetitive inspections required by paragraph 

(g) of this AD, provided that after the hinge 

bracket replacement, but before further flight 

after the effective date of this AD, a one-time 

detailed inspection of the forward and aft 

outer shroud box has been done with no 

cracking found, in accordance with 

paragraph (g) of this AD. The replacement 

must be done in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or EASA; or Airbus’s EASA 

DOA. 

(k) Credit for Previous Actions 

This paragraph provides credit for 

inspections required by paragraph (g) of this 

AD, if those actions were performed before 

the effective date of this AD using any of the 

applicable service information listed in 

paragraphs (k)(1) through (k)(8) of this AD. 

(1) Airbus Service Bulletin A300–57–142, 

dated December 17, 1986. 

(2) Airbus Service Bulletin A300–57–142, 

Revision 1, dated April 9, 1990. 

(3) Airbus Service Bulletin A300–57–142, 

Revision 2, dated January 16, 1991. 

(4) Airbus Service Bulletin A300–57–0142, 

Revision 03, dated February 22, 1999. 

(5) Airbus Service Bulletin A300–57–6010, 

Revision 1, dated December 14, 1990. 

(6) Airbus Service Bulletin A300–57–6010, 

Revision 02, dated March 30, 1998. 

(7) Airbus Service Bulletin A300–57–6010, 

Revision 03, dated September 16, 1998. 

(8) Airbus Service Bulletin A300–57–6010, 

Revision 04, dated February 22, 1999. 

(l) 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: 

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. 

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; 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0181R1, dated 

August 20, 2013, 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–2015–6550. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(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. 


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63374 Federal Register / Vol. 81, No. 179 / Thursday, September 15, 2016 / Rules and Regulations 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A300–57–0142, 

Revision 04, dated March 30, 2011. 

(ii) Airbus Service Bulletin A300–57–143, 

Revision 2, dated July 10, 1989. Pages 1, 3, 

4, 7, 10, 13, and 14 of this document are 

identified as Revision 2, dated July 10, 1989; 

pages 2 and 8 are identified as original, dated 

December 12, 1986; and pages 5, 6, 9, 11, 12, 

and 15 are identified as Revision March 19, 

1987. 

(iii) Airbus Service Bulletin A300–57– 

6010, Revision 05, dated February 21, 2011. 

(iv) Airbus Service Bulletin A300–57– 

6011, Revision 2, dated July 10, 1989. Pages 

1, 2, 5, 7, 8, 11, and 12 of this document are 

identified as Revision 2, dated July 10, 1989; 

pages 3, 4, and 13 are identified as Revision 

1, dated March 19, 1987; and pages 6, 9, 10 

are identified as original, dated December 17, 

1986. 

(3) For service information identified in 

this AD, 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. 

(4) 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. 

(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 Renton, Washington, on August 

24, 2016. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–21146 Filed 9–14–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3781; Directorate 

Identifier 2015–SW–048–AD; Amendment 

39–18649; AD 2016–18–18] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Agusta 

S.p.A. (Agusta) Model A109A, A109A II, 

A109C, A109E, A109K2, A109S, and 

AW109SP helicopters. This AD requires 

visually inspecting the tail rotor drive 

shaft assembly (drive shaft) for a crack. 

This AD was prompted by the discovery 

of three cracks on the drive shaft of a 

Model A109S helicopter. The actions of 

this AD are intended to detect a crack 

on the drive shaft to prevent failure of 

the driveshaft, failure of the tail rotor, 

and subsequent loss of helicopter 

control. 

DATES: This AD is effective October 20, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of October 20, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

AgustaWestland, Product Support 

Engineering, Via del Gregge, 100, 21015 

Lonate Pozzolo (VA) Italy, ATTN: 

Maurizio D’Angelo; telephone 39–0331– 

664757; fax 39–0331–664680; or at 

http://www.agustawestland.com/ 

technical-bulletins. You may review the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy, Room 6N–321, Fort Worth, TX 

76177. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2015–3781. 

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– 

3781; 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 European Aviation 

Safety Agency (EASA) AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Martin R. Crane, Aviation Safety 

Engineer, Safety Management Group, 

Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy, Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

martin.r.crane@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On March 22, 2016, at 81 FR 15171, 

the Federal Register published our 

notice of proposed rulemaking (NPRM), 

which proposed to amend 14 CFR part 

39 by adding an AD that would apply 

to Agusta S.p.A. Model A109A, A109A 

II, A109C, A109E, A109K2, A109S, and 

AW109SP helicopters with a drive shaft 

part number (P/N) 109–8412–02–1 or 

109–8412–02–3 installed. The NPRM 

proposed to require visually inspecting 

the drive shaft for a crack. The proposed 

requirements were intended to detect a 

crack on the drive shaft to prevent 

failure of the driveshaft, failure of the 

tail rotor, and subsequent loss of 

helicopter control. 

The NPRM was prompted by AD No. 

2015–0054, dated March 27, 2015, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for the Model A109A with 

retrofit kit P/N 109–0820–27–101 

installed, and Model A109A II, A109C, 

A109E, A109K2, A109LUH, A109S, and 

AW109SP helicopters. 

EASA advises that during scheduled 

maintenance on a Model A109S 

helicopter, three cracks were found on 

the drive shaft. An investigation could 

not determine the cause of the cracking 

but concluded it could not have been 

caused by fatigue. This condition, if not 

detected and corrected, could lead to 

tail rotor failure, possibly resulting in 

loss of helicopter control, EASA 

advises. EASA AD No. 2015–0054 

consequently requires a one-time 

inspection of the drive shaft, and 

replacing the drive shaft if cracks are 

found. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(81 FR 15171, March 22, 2016). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Italy and are 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Italy, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

Interim Action 

We consider this AD to be an interim 

action. The design approval holder has 

not determined the cause of the unsafe 


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