Federal Register / Vol. 78, No. 95 / Thursday, May 16, 2013 / Rules and Regulations 28727 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2013–10–01 Spectrolab Nightsun XP 

Searchlight: Amendment 39–17454; 

Docket No. FAA–2012–0221; Directorate 

Identifier 2010–SW–082–AD. 

(a) Applicability 

This AD applies to Spectrolab Nightsun XP 

Searchlight Assembly Systems with gimbal 

assembly part number (P/N) 033295–1 or 

033295–2, installed on, but not limited to, 

Agusta S.p.A. Model AB139 and Model 

AW139 helicopters, Sikorsky Aircraft 

Corporation Model S–92A helicopters, and 

Eurocopter Deutschland GmbH Model EC135 

and Model MBB–BK 117 C–2 helicopters, 

certificated in any category. The searchlight 

assembly system P/Ns and revision level 

using one of the two affected gimbal 

assembly P/Ns are listed in Table 1 to 

Paragraph (a) of this AD. 

TABLE 1 TO PARAGRAPH (A)—AFFECTED SYSTEMS AND P/N 

System P/N Nomenclature Affected 

revisions 

033338 ...................................... Nightsun XP Searchlight System .................................................................................................. A through D. 

033338–3 .................................. Nightsun XP Searchlight System .................................................................................................. A through D. 

033338–4 .................................. Nightsun XP Searchlight System .................................................................................................. A through D. 

033704 ...................................... IFCO Nightsun XP Searchlight System ......................................................................................... A through C. 

033704–1 .................................. IFCO Nightsun XP Searchlight System ......................................................................................... A through C. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

the Searchlight/Gimbal disconnecting from 

the helicopter and remaining attached solely 

by the internal cable harness, or separating 

totally. This condition could result in 

damage to the helicopter and injury to 

persons on the ground. 

(c) Effective Date 

This AD becomes effective June 20, 2013. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) Before further flight, insert a copy of 

Nightsun XP Searchlight Safety and Service 

Bulletin No. SL 0810–01, Amendment No. 2, 

dated September 24, 2010, into the Normal 

Procedures section of the Rotorcraft Flight 

Manual. 

(2) Before the first flight of each day, 

visually check the searchlight installation for 

a gap between the top shroud rubber edging, 

P/N 033381, and the side covers, P/N 033286, 

with slight pressure applied to either side of 

the searchlight. The edging must remain in 

physical contact with the side covers when 

slight pressure is applied to the searchlight. 

(3) The actions required by paragraph (e)(2) 

of this AD may be performed by the owner/ 

operator (pilot) holding at least a Private Pilot 

Certificate, and must be entered into the 

helicopter maintenance records in 

accordance with 14 CFR 43.9(a)(1)–(4) and 

91.417(a)(2)(v). The record must be 

maintained as required by 14 CFR 91.417, 

121.380, or 135.439. 

(4) If the edging does not remain in 

physical contact with the side cover when 

slight pressure is applied to the searchlight 

in accordance with the requirements of 

paragraph (e)(2) of this AD, before further 

flight, with an affected Spectrolab Nightsun 

XP Searchlight assembly system installed, 

modify and re-identify the gimbal assembly 

in accordance with paragraph (e)(5) of this 

AD. 

(5) Within 100 hours time-in-service, 

modify and re-identify the gimbal assembly 

in accordance with Nightsun XP Searchlight 

System Kit and Procedure to Incorporate 

EASA AD 2010–0183 Conformance, 034374 

Revision NC, approved September 28, 2010, 

steps 1 through 13. 

(6) Accomplishing paragraph (e)(5) of this 

AD is terminating action for the requirements 

of this AD. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Fuller, 

Senior Aviation Safety Engineer, Safety 

Management Group, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5110; 

email matthew.fuller@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2010–0237R2, dated December 14, 2010. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 3340, Exterior lighting. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the following service information under 5 

U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use this information as 

applicable to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Nightsun XP Searchlight Safety and 

Service Bulletin No. SL 0810–01, 

Amendment No. 2, dated September 24, 

2010. 

(ii) Nightsun XP Searchlight System Kit 

and Procedure to Incorporate EASA AD 

2010–0183 Conformance, 034374 Revision 

NC, dated September 28, 2010. The date of 

this document is identified only in the 

Change Record on page 2 of this service 

information. 

(3) For Spectrolab Nightsun XP Searchlight 

service information identified in this AD, 

contact Spectrolab, Inc. ATTN: Saul Vargas, 

12500 Gladstone Ave., Sylmar, CA 91342, 

telephone (818) 365–4611, fax (818) 361– 

5102, or on the internet at http:// 

www.spectrolab.com. 

(4) You may review a copy of the service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(5) You may also review a copy of 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/ibr-locations.html. 

Issued in Fort Worth, Texas, on April 26, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–11383 Filed 5–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0695; Directorate 

Identifier 2011–SW–031–AD; Amendment 

39–17448; AD 2013–09–06] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 


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28728 Federal Register / Vol. 78, No. 95 / Thursday, May 16, 2013 / Rules and Regulations 

Agusta S.p.A. (Agusta) Model A119 and 

AW119 MKII helicopters. The existing 

AD currently requires inspecting the 

pilot and copilot engine rotary variable 

differential transformer (RVDT) control 

box assemblies to determine if the 

control gear locking pin is in its proper 

position. Since we issued that AD, 

Agusta has developed a terminating 

action for this inspection. This AD 

requires the same actions as the existing 

AD as well as modifying the RVDT 

control box assemblies. The actions of 

this AD are intended to prevent failure 

of an RVDT control box assembly, loss 

of manual control of the engine throttle, 

and subsequent loss of control of the 

helicopter. 

DATES: This AD is effective June 20, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of June 20, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Agusta 

Westland, Customer Support & Services, 

Via Per Tornavento 15, 21019 Somma 

Lombardo (VA) Italy, Attn: Giovanni 

Cecchelli; telephone 39 0331711133; fax 

39 0331 711180; or at http:// 

www.agustawestland.com/technicalbullettins. You may review the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov 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, 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: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On July 3, 2012, at 77 FR 39444, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 to 

supersede AD 2010–15–51 (75 FR 

50863, August 18, 2010). The NPRM 

would apply to Agusta model A119 and 

AW119 MKII helicopters and proposed 

to require repetitively inspecting the 

pilot and co-pilot control box 

assemblies for the proper positioning of 

the locking pins, and if the locking pin 

is recessed or extended in excess of 2.0 

millimeters from the face of the pin 

bore, or missing, replacing the control 

box assembly. Additionally, the NPRM 

proposed to require modifying the pilot 

and co-pilot control box assemblies to 

terminate the repetitive inspection 

requirements. The proposed 

requirements were intended to prevent 

failure of an RVDT control box 

assembly, loss of manual control of the 

engine throttle, and subsequent loss of 

control of the helicopter. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2011– 

0095–E, dated May 24, 2011, to 

permanently correct the unsafe 

condition addressed in AD 2010–15–51 

(75 FR 50863, August 18, 2010) for the 

Agusta A119 and AW MKII helicopters. 

EASA advises that Agusta has 

developed a modification to the pilot 

and co-pilot control box assemblies that 

will ‘‘remedy the problem and prevent 

recurrence.’’ This EASA AD requires 

repetitive inspections of the affected 

pilot and co-pilot control box 

assemblies until a terminating action 

modification is made within 8 calendar 

months of the effective date of the EASA 

AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (77 FR 39444, July 3, 2012). 

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. 

Related Service Information 

We reviewed Agusta Alert Bollettino 

Tecnico (ABT) No. 119–39 Revision A, 

dated May 23, 2011 (ABT 119–39). The 

ABT 119–39 describes procedures for 

repetitively inspecting the pilot and copilot control box assemblies for correct 

positioning of the engine RVDT control 

gear locking pin and provides 

instructions on how to modify the pilot 

and co-pilot control box assemblies to 

terminate the repetitive inspections. 

EASA classified this ABT as mandatory 

and issued EAD No. 2011–0095–E, 

dated May 24, 2011, to ensure the 

continued airworthiness of these 

helicopters. 

Costs of Compliance 

We estimate that this AD will affect 

49 helicopters of U.S. Registry. We 

estimate that operators will incur the 

following costs in order to comply with 

this AD. At an average labor rate of $85 

per work hour, inspecting the two RVDT 

control box assemblies will require 

about 1.5 hours, for a cost per helicopter 

of about $128 and a cost to the U.S. fleet 

of about $6,272 per inspection cycle. 

Modification of the pilot and co-pilot 

RVDT control box assemblies will 

require about 8 hours, and required 

parts will cost about $8, for a total cost 

per helicopter of $688 and a cost to the 

U.S. fleet of $33,712. 

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 

helicopters identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 


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Federal Register / Vol. 78, No. 95 / Thursday, May 16, 2013 / Rules and Regulations 28729 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I certify 

that this AD: 

(1) Is not a ‘‘significant regulatory action’’ 

under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under DOT 

Regulatory Policies and Procedures (44 FR 

11034, February 26, 1979); 

(3) Will not affect intrastate aviation in 

Alaska to the extent that it justifies making 

a regulatory distinction; 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. 

We prepared an economic evaluation of the 

estimated costs to comply with this AD and 

placed it in the AD docket. 

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) 

2010–15–51, Amendment 39–16397 (75 

FR 50863, August 18, 2010), and adding 

the following new AD: 

2013–09–06 Agusta S.p.A.: Amendment 39– 

17448; Docket No. FAA–2012–0695; 

Directorate Identifier 2011–SW–031–AD. 

(a) Applicability 

This AD applies to Agusta Model A119 and 

AW119 MKII helicopters, with pilot control 

box assembly (control box), part number 

(P/N) 109–0010–81–103, and co-pilot control 

box, P/N 109–0010–81–107, installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

rotary variable differential transformer 

(RVDT) locking pin, which could move out 

of position and result in loss of manual 

throttle control of the engine and subsequent 

loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2010–15–51, 

Amendment 39–16397 (75 FR 50863, August 

18, 2010). 

(d) Effective Date 

This AD becomes effective June 20, 2013. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

(1) Within 5 hours time-in-service (TIS), 

and thereafter at intervals not to exceed 50 

hours TIS, remove the cover of the pilot and 

co-pilot RVDT control box assemblies and 

inspect the locking pins for proper position 

by following the Compliance Instructions, 

Parts I and II, paragraphs 2. through 4.1 for 

the pilot control box assembly and 

paragraphs 5. through 7.1 for the co-pilot 

control box assembly, of Agusta Bollettino 

Tecnico No. 119–39, Revision A, dated May 

23, 2011. 

(2) If during the inspection the locking pin 

is recessed or extended in excess of 2.0 

millimeters from the face of the pin bore, or 

missing, before further flight, replace the 

RVDT control box with an airworthy RVDT 

control box that has been modified in 

accordance with paragraph (f)(3) of this AD. 

(3) Within 8 months, 

(i) Modify the pilot RVDT control box 

assembly, P/N 109–0010–81–103, by 

reference to Figures 1 through 7 and in 

accordance with the Compliance 

Instructions, Part III, paragraphs 5.1 through 

5.16 of Agusta Bollettino Tecnico No. 119– 

39 Revision A, dated May 23, 2011; and 

(ii) Modify the co-pilot RVDT control box 

assembly, P/N 109–0010–81–107, by 

reference to Figures 1 through 7 and in 

accordance with the Compliance 

Instructions, Part III, paragraphs 3.1 through 

3.16 of Agusta Bollettino Tecnico No. 119– 

39, Revision A, dated May 23, 2011. 

(4) Modifying the pilot and copilot RVDT 

control box assemblies in accordance with 

paragraph (f)(3) of this AD constitutes 

terminating action for the requirements of 

this AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, FAA, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone (817) 222– 

5110; email robert.grant@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency AD 2011– 

0095–E, dated May 24, 2011. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6700: Rotors Flight Control. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Agusta Bollettino Tecnico No. 119–39 

Revision A, dated May 23, 2011. 

(ii) Reserved. 

(3) For Agusta service information 

identified in this AD, contact Agusta 

Westland, Customer Support & Services, Via 

Per Tornavento 15, 21019 Somma Lombardo 

(VA) Italy, ATTN: Giovanni Cecchelli; 

telephone 39–0331–711133; fax 39 0331 

711180; or at http:// 

www.agustawestland.com/technicalbullettins. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on April 26, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–10903 Filed 5–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1109; Directorate 

Identifier 2011–NM–172–AD; Amendment 

39–17455; AD 2013–10–02] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain The Boeing Company Model 

757–200 and –200PF series airplanes. 

That AD currently requires modifying 

the nacelle strut and wing structure, and 

repairing any damage found during the 

modification. This new AD specifies a 

maximum compliance time limit that 

overrides the optional threshold formula 

results. This AD was prompted by 

reports indicating that the actual 

operational loads applied to the nacelle 

are higher than the analytical loads that 


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