3316 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 

telephone +44(0)2890–462469; fax 

+44(0)2890 468444; email 

michael.mulholland@aero.bombardier.com; 

Internet http://www.bombardier.com. 

(5) 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. 

(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 

4, 2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00378 Filed 1–20–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1422; Directorate 

Identifier 2014–NM–125–AD; Amendment 

39–18370; AD 2016–01–11] 

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) 98–18–26, 

for certain Airbus Model A320 series 

airplanes. AD 98–18–26 required 

repetitive inspections to detect fatigue 

cracking of the front spar vertical 

stringers on the wings; and repair, if 

necessary. This new AD requires 

repetitive high frequency eddy current 

(HFEC) inspections for cracking of the 

radius of the front spar vertical stringers 

and the horizontal floor beam on frame 

36, a rototest inspection for cracking of 

the fastener holes of the front spar 

vertical stringers on frame 36, and repair 

if necessary. This AD was prompted by 

reports that indicate new repetitive 

inspections having new thresholds and 

intervals are needed and that additional 

work is needed to accomplish the 

inspections on airplanes on which a 

previous modification has been 

accomplished. We are issuing this AD to 

detect and correct fatigue cracking of the 

front spar vertical stringers on the 

wings, which could result in the 

reduced structural integrity of the 

airframe. 

DATES: This AD becomes effective 

February 25, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 25, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-1422; or in 

person at the 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. 

For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 

61 93 44 51; email account.airwortheas@airbus.com; Internet http://

www.airbus.com. 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–2015–1422. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 98–18–26, 

Amendment 39–10742 (63 FR 47423, 

September 8, 1998). AD 98–18–26 

applied to certain Airbus Model A320 

series airplanes. The NPRM published 

in the Federal Register on June 5, 2015 

(80 FR 32063). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0069, dated March 19, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on certain Airbus 

Model A320–211, –212, and –231 

airplanes. The MCAI states: 

During center fuselage certification full 

scale fatigue test, cracks were found on the 

front vertical stringer at frame 36. Analysis of 

these findings indicated that a number of inservice aeroplanes could be similarly 

affected. 

This condition, if not detected and 

corrected, could lead to crack propagation 

and consequent deterioration of the 

structural integrity of the aeroplane. 

To address this potential unsafe condition, 

[Directorate General for Civil Aviation] 

DGAC France AD 97–311–105 [which 

corresponds to FAA AD 98–18–26, 

Amendment 39–10742 (63 FR 47423, 

September 8, 1998)] was issued to require 

repetitive [HFEC] inspections [for cracking] 

in accordance with the instruction of Airbus 

Service Bulletin (SB) A320–57–1016. At the 

same time, the modification provided by 

Airbus SB A320–57–1017 was considered to 

be terminating action for the repetitive 

inspections required by DGAC France AD 

97–311–105. 

Since that [DGAC] AD was issued, and 

following new analysis, modification per 

Airbus SB A320–57–1017 is no longer 

considered to be terminating action for the 

repetitive inspections as required by DGAC 

France AD 97–311–105. 

Aeroplanes with [manufacturer serial 

number] MSN 0080 up to 0155 inclusive 

have been delivered with the addition of a 5 

[millimeter] mm thick light alloy shim under 

the heads of 2 fasteners at the top end of the 

front spar vertical stringers (Airbus 

modification 21290P1546, which is the 

production line equivalent to in-service 

modification through Airbus SB A320–57– 

1017). From MSN 0156 and higher, all 

aeroplanes are delivered with vertical 

stiffeners of the forward wing spar upper end 

with stiffener cap thickness increased from 4 

to 6 mm (Airbus modification 21290P1547). 

Prompted by these findings, Airbus issued 

SB A320–57–1178 to introduce new 

repetitive inspections with new thresholds 

and intervals. 

For the reasons described above, DGAC 

France AD 97–311–105 is superseded and 

this [EASA] AD requires the repetitive 

inspections at new thresholds and intervals. 

After EASA issued [proposed 

airworthiness directive] PAD 14–021, it was 

discovered that additional work [HFEC 

inspections for cracking of the radius of spar 

vertical stringers and horizontal beam in the 

center fuselage of frame 36, and a rototest 

inspection for cracking of the fastener holes 

of the spar vertical stringers radius on Frame 

36 and repair if necessary], to be included in 

Revision 01 of Airbus SB A320–57–1178, is 

required to accomplish the inspections. This 

Final [EASA] AD has been amended 

accordingly. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-1422- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (80 FR 32063, 

June 5, 2015) and the FAA’s response to 

the comments. 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 3317 

Requests for Clarification of Certain 

Requirements 

Delta Airlines (DAL) asked that we 

move the repetitive inspection intervals 

from paragraph (g) of the proposed AD 

(80 FR 32063, June 5, 2015), and create 

a new paragraph (i) with the repetitive 

inspection intervals. DAL stated that 

having the inspection method and the 

repetitive inspection intervals in one 

paragraph, as well as a separate 

paragraph for the initial inspection is 

cumbersome. 

We do not agree with the requested 

changes. We re-examined the structure 

of the regulatory text of this AD, and 

have determined that the specified 

language as proposed is clear and aligns 

with the MCAI. Therefore, we have not 

changed this AD in this regard. 

DAL also asked that we add sub-steps 

to requirements in the proposed AD (80 

FR 32063, June 5, 2015), to clarify the 

inspection requirements specified in 

Airbus Service Bulletin A320–57–1178, 

Revision 01, dated May 28, 2014. 

We do not agree. Our goal in referring 

to the Accomplishment Instructions of 

the service information is to ensure that 

operators follow the details in the 

inspection steps shown therein. DAL 

has the option of creating task cards if 

it makes accomplishing the sub-steps 

easier, provided the cards meet the 

intent of the AD. We have not changed 

this AD in this regard. 

Additionally, DAL asked that 

Appendix 01 of Airbus Service Bulletin 

A320–57–1178, Revision 01, dated May 

28, 2014, be removed from the service 

bulletin identification in the NPRM (80 

FR 32063, June 5, 2015), because 

Appendix 01 has Gantt Chart 

information that should not be 

highlighted as a regulatory requirement 

for compliance. 

We do not agree. The information in 

Appendix 01 of Airbus Service Bulletin 

A320–57–1178, Revision 01, dated May 

28, 2014, may be helpful to operators 

that want to determine the number of 

work hours necessary to accomplish 

specific actions. Moreover, Appendix 01 

does not contain a requirement for 

compliance. We have not changed this 

AD in this regard. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, with minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 

32063, June 5, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 32063, 

June 5, 2015). 

We have also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–57–1178, Revision 01, dated May 

28, 2014, including Appendix 01, dated 

May 28, 2014. The service information 

describes procedures for inspecting the 

radius of the front spar vertical stringers 

and the horizontal floor beam on frame 

36 for cracking. 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 17 

airplanes of U.S. registry. 

We also estimate that it will take 

about 24 work-hours per product to 

comply with the basic requirements of 

this AD. 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 $34,680, or $2,040 per 

product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 49 work-hours and require parts 

costing $1,210, for a cost of $5,375 per 

product. We have no way of 

determining the number of aircraft that 

might need this action. 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/#!docket

Detail;D=FAA-2015-1422; 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. 

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) 

98–18–26, Amendment 39–10742 (63 

FR 47423, September 8, 1998), and 

adding the following new AD: 

2016–01–11 Airbus: Amendment 39–18370. 

Docket No. FAA–2015–1422; Directorate 

Identifier 2014–NM–125–AD. 


jstallworth on DSK7TPTVN1PROD with RULES
3318 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 

(a) Effective Date 

This AD becomes effective February 25, 

2016. 

(b) Affected ADs 

This AD replaces AD 98–18–26, 

Amendment 39–10742 (63 FR 47423, 

September 8, 1998). 

(c) Applicability 

This AD applies to Airbus Model A320– 

211, –212, and –231 airplanes, certificated in 

any category, manufacturer serial numbers 

(MSN) 0001 through 0155 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by cracks found on 

the front vertical stringer at frame 36. This 

AD was also prompted by reports that 

indicate new repetitive inspections having 

new thresholds and intervals are needed and 

that additional work is needed to accomplish 

the inspections on airplanes on which a 

previous modification has been 

accomplished. We are issuing this AD to 

detect and correct fatigue cracking of the 

front spar vertical stringers on the wings, 

which could result in the reduced structural 

integrity of the airframe. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections 

Within the applicable compliance times 

specified in paragraphs (h)(1) through (h)(4) 

of this AD, do a high frequency eddy current 

(HFEC) inspection for cracking of the radius 

of the front spar vertical stringers and the 

horizontal floor beam on frame 36, and do a 

rototest inspection for cracking of the 

fastener holes of the front spar vertical 

stringers on frame 36, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1178, Revision 01, 

dated May 28, 2014, including Appendix 01, 

dated May 28, 2014. Repeat the inspections 

thereafter at the compliance times specified 

in paragraphs (g)(1) and (g)(2) of this AD. 

(1) For Configuration 1 airplanes identified 

in paragraph (h)(1) of this AD: At intervals 

not to exceed 8,800 flight cycles or 17,700 

flight hours, whichever occurs first. 

(2) For Configuration 2, 3, and 4 airplanes 

identified in paragraphs (h)(2) through (h)(4) 

of this AD: At intervals not to exceed 24,900 

flight cycles or 49,800 flight hours, 

whichever occurs first. 

(h) Compliance Times for Initial Inspections 

Required by Paragraph (g) of This AD 

Do the initial inspections required by 

paragraph (g) of this AD within the 

applicable compliance times specified in 

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

(1) For Configuration 1 airplanes, having 

MSNs 0001 through MSN 0079 inclusive, on 

which the modification specified by Airbus 

Service Bulletin A320–57–1017, dated 

September 3, 1991; or Airbus Service 

Bulletin A320–57–1017, Revision 01, dated 

March 17, 1997, has not been accomplished: 

Inspect at the later of the times specified by 

paragraphs (h)(1)(i) through (h)(1)(iii) of this 

AD. 

(i) Inspect at the later of the times specified 

by paragraphs (h)(1)(i)(A) and (h)(1)(i)(B) of 

this AD. 

(A) Prior to the accumulation of 24,000 

flight cycles or 48,000 flight hours, 

whichever occurs first since airplane first 

flight. 

(B) Within 60 days after the effective date 

of this AD. 

(ii) Inspect within 8,800 flight cycles or 

17,700 flight hours, whichever occurs first, 

since the last inspection specified in Airbus 

Service Bulletin A320–57–1016 was 

accomplished. 

(iii) Inspect within 850 flight cycles or 

1,700 flight hours, whichever occurs first, 

after the effective date of this AD, without 

exceeding 14,000 flight cycles after the last 

inspection specified in Airbus Service 

Bulletin A320–57–1016 was accomplished. 

(2) For Configuration 2 airplanes, having 

MSNs 0001 through 0079 inclusive, on 

which the actions specified by Airbus 

Service Bulletin A320–57–1016, have not 

been done prior to accomplishing the actions 

specified by Airbus Service Bulletin A320– 

57–1017, dated September 3, 1991; or Airbus 

Service Bulletin A320–57–1017, Revision 01, 

dated March 17, 1997: Inspect at the later of 

the times specified by paragraphs (h)(2)(i) 

and (h)(2)(ii) of this AD. 

(i) Within 8,800 flight cycles or 17,700 

flight hours, whichever occurs first, since the 

modification specified in Airbus Service 

Bulletin A320–57–1017, dated September 3, 

1991; or Airbus Service Bulletin A320–57– 

1017, Revision 01, dated December 6, 1995, 

was accomplished. 

(ii) Within 850 flight cycles or 1,700 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

(3) For Configuration 3 airplanes, having 

MSNs 0001 through 0079 inclusive, on 

which the actions specified by Airbus 

Service Bulletin A320–57–1016, have been 

done prior to accomplishing the actions 

specified by Airbus Service Bulletin A320– 

57–1017, dated September 3, 1991; or Airbus 

Service Bulletin A320–57–1017, Revision 01, 

dated March 17, 1997: Inspect at the later of 

the times specified by paragraphs (h)(3)(i) 

and (h)(3)(ii) of this AD. 

(i) Within 24,900 flight cycles or 49,800 

flight hours, whichever occurs first, since the 

modification specified in Airbus Service 

Bulletin A320–57–1017, dated September 3, 

1991; or Airbus Service Bulletin A320–57– 

1017, Revision 01, dated March 17, 1997, was 

accomplished. 

(ii) Within 850 flight cycles or 1,700 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

(4) For Configuration 4 airplanes, having 

MSNs 0080 through 0155 inclusive: Inspect 

at the later of the times specified in 

paragraphs (h)(4)(i) or (h)(4)(ii) of this AD. 

(i) Prior to the accumulation of 54,300 

flight cycles or 108,600 flight hours, 

whichever occurs first since airplane first 

flight. 

(ii) Within 60 days after the effective date 

of this AD. 

(i) Repair 

If any crack is detected during any 

inspection required by paragraph (g) of this 

AD: 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). 

(j) 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; 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. The AMOC approval letter 

must specifically reference this AD. 

(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 EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0069, dated 

March 19, 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– 

2015–1422. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on February 25, 2016. 

(i) Airbus Service Bulletin A320–57–1178, 

Revision 01, dated May 28, 2014, including 

Appendix 01, dated May 28, 2014. 

(ii) Reserved. 

(4) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 3319 

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. 

(5) 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. 

(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 

December 31, 2015. 

Philip Forde, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00373 Filed 1–20–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1998; Directorate 

Identifier 2014–SW–035–AD; Amendment 

39–18379; AD 2016–01–19] 

RIN 2120–AA64 

Airworthiness Directives; MD 

Helicopters Inc. 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for MD 

Helicopters Inc. (MDHI) Model 500N 

and 600N helicopters with certain 

rotating cone assemblies installed. This 

AD requires establishing a life limit of 

10,000 hours time-in-service (TIS) on 

these rotating cone assemblies. This AD 

was prompted by the determination that 

MDHI created rotating cone assemblies 

with new dash numbers but incorrectly 

failed to identify them as life-limited 

parts. The actions are intended to 

prevent operation of rotating cone 

assemblies past their life limits, failure 

of the rotating cone assemblies, loss of 

directional control, and subsequent loss 

of control of the helicopter. 

DATES: This AD is effective February 25, 

2016. 

ADDRESSES: For service information 

identified in this final rule, contact MD 

Helicopters, Inc., Attn: Customer 

Support Division, 4555 E. McDowell 

Rd., Mail Stop M615, Mesa, AZ 85215– 

9734; telephone 1–800–388–3378; fax 

480–346–6813; or at http://

www.mdhelicopters.com. You may 

review a copy of the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy, Room 6N–321, 

Fort Worth, TX 76177. 

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– 

1998; 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 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: 

Galib Abumeri, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

Transport Airplane Directorate, FAA, 

3960 Paramount Blvd., Lakewood, 

California 90712, telephone 562–627– 

5324; email Galib.Abumeri@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On June 9, 2015, at 80 FR 32508, 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 

MDHI Model 500N helicopters with a 

rotating cone assembly part number (P/ 

N) 500N3740–81 installed, and Model 

600N helicopters with a rotating cone 

assembly P/N 500N3740–71 installed. 

The NPRM proposed to require 

establishing a life limit of 10,000 hours 

TIS on these rotating cone assemblies. 

Although these parts have a life limit of 

10,000 hours TIS, they were incorrectly 

omitted from the Airworthiness 

Limitation Section of the Rotorcraft 

Maintenance Manual. Some of the 

affected parts were sold as spares, while 

others were installed on new helicopters 

in production. The proposed 

requirements were intended to prevent 

operation of rotating cone assemblies 

past their life limits, failure of the 

rotating cone assemblies, loss of 

directional control, and subsequent loss 

of control of the helicopter. 

Since the NPRM was issued, the FAA 

Southwest Regional Office has 

relocated. This AD includes the current 

physical address of the FAA Southwest 

Regional Office. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(80 FR 32508, June 9, 2015). 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

Related Service Information 

MDHI issued Service Bulletin 

SB500N–046 and SB600N–054 (SB) as a 

single bulletin on July 9, 2012. The SB 

calls for a one-time inspection within 

100 flight hours to determine the 

rotating cone assembly’s part number on 

MDHI Model 500N and 600N 

helicopters. The SB then states the need 

to correct the component record for 

certain rotating cone assemblies. 

The SB also specifies determining the 

rotating cone assembly’s total service 

time since new and recording this on 

the component record. MDHI reports 

that failure to comply with the SB may 

result in an aircraft exceeding the life 

limit of the rotating cone assembly and 

that this could lead to component 

failure and loss of directional control of 

the helicopter. 

Differences Between This AD and the 

Service Information 

The SB calls for inspecting the 

rotating cone assembly to determine its 

P/N. We make no requirement about 

how to determine the P/N. The 

compliance time for the SB is within 

100 flight hours, while this AD requires 

compliance within 1 year or by the next 

annual inspection, whichever comes 

later. 

Costs of Compliance 

We estimate that this AD affects 8 

helicopters of U.S. Registry and that 

labor costs average $85 a work hour. We 

estimate that creating a component 

history card and revising the 

appropriate records takes 1 work-hour. 

No parts are needed for a total cost of 

$85 per helicopter and $680 for the U.S. 

fleet. 

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 


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