Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations 72505 

compact fluorescent lamps, or integrated LED 

lamps. 

2. Definitions: 

Measured initial input power means the 

input power to the lamp, measured after the 

lamp is stabilized and seasoned (if 

applicable), and expressed in watts (W). 

Measured initial lumen output means the 

lumen output of the lamp, measured after the 

lamp is stabilized and seasoned (if 

applicable), and expressed in lumens (lm). 

Power factor means the measured initial 

input power (watts) divided by the product 

of the input voltage (volts) and the input 

current (amps) measured at the same time as 

the initial input power. 

3. Active Mode Test Procedures 

3.1. Take measurements at full light 

output. 

3.2. Do not use a goniophotometer. 

3.3. For single base OLED and nonintegrated LED lamps, position a lamp in 

either the base-up and base-down orientation 

throughout testing. Test an equal number of 

lamps in the sample in the base-up and basedown orientations, except that, if the 

manufacturer restricts the orientation, test all 

of the units in the sample in the 

manufacturer-specified orientation. For 

double base OLED and non-integrated LED 

lamps, test all units in the horizontal 

orientation except that, if the manufacturer 

restricts the orientation, test all of the units 

in the sample in the manufacturer-specified 

orientation. 

3.4. Operate the lamp at the rated voltage 

throughout testing. For lamps with multiple 

rated voltages including 120 volts, operate 

the lamp at 120 volts. If a lamp is not rated 

for 120 volts, operate the lamp at the highest 

rated input voltage. For non-integrated LED 

lamps, operate the lamp at the manufacturerdeclared input voltage and current. 

3.5. Operate the lamp at the maximum 

input power. If multiple modes occur at the 

same maximum input power (such as 

variable CCT or CRI), the manufacturer may 

select any of these modes for testing; 

however, all measurements must be taken at 

the same selected mode. The manufacturer 

must indicate in the test report which mode 

was selected for testing and include detail 

such that another laboratory could operate 

the lamp in the same mode. 

3.6. To measure initial lumen output, input 

power, input voltage, and input current use 

the test procedures in the table in this 

section. 

TABLE 3.1—REFERENCES TO INDUSTRY STANDARD TEST PROCEDURES

Lamp type Referenced test procedure 

General service incandescent lamps ....................................................... Appendix R to subpart B of 10 CFR part 430. 

Compact fluorescent lamps ...................................................................... Appendix W to subpart B of 10 CFR part 430. 

Integrated LED lamps ............................................................................... Appendix BB to subpart B of 10 CFR part 430. 

Other incandescent lamps that are not reflector lamps ........................... IES LM–45–15, sections 4–6, and section 7.1.* 

Other incandescent lamps that are reflector lamps ................................. IES LM–20–13, sections 4–6, and section 8.* 

Other fluorescent lamps ........................................................................... IES LM–9–09–DD, sections 4–6, and section 7.5.* 

OLED lamps ............................................................................................. IES LM–79–08–DD, sections 1.3 (except 1.3f), 2.0, 3.0, 5.0, 7.0, 8.0, 

9.1 and 9.2.* 

Non-integrated LED lamps ....................................................................... IES LM–79–08–DD, sections 1.3 (except 1.3f), 2.0, 3.0, 5.0, 7.0, 8.0, 

9.1 and 9.2.* 

* Incorporated by reference, see § 430.3. 

3.7. Determine initial lamp efficacy by 

dividing the measured initial lumen output 

(lumens) by the measured initial input power 

(watts). 

3.8. Determine power factor by dividing 

the measured initial input power (watts) by 

the product of the measured input voltage 

(volts) and measured input current (amps). 

4. Standby Mode Test Procedure 

4.1. Measure standby mode power only for 

lamps that are capable of standby mode 

operation. 

4.2. Maintain lamp orientation as specified 

in section 3.3 of this appendix. 

4.3. Connect the lamp to the manufacturerspecified wireless control network (if 

applicable) and configure the lamp in 

standby mode by sending a signal to the lamp 

instructing it to have zero light output. Lamp 

must remain connected to the network 

throughout testing. 

4.4. Operate the lamp at the rated voltage 

throughout testing. For lamps with multiple 

rated voltages including 120 volts, operate 

the lamp at 120 volts. If a lamp is not rated 

for 120 volts, operate the lamp at the highest 

rated input voltage. 

4.5. Stabilize the lamp prior to 

measurement as specified in section 5 of IEC 

62301–DD (incorporated by reference; see 

§ 430.3). 

4.6. Measure the standby mode power in 

watts as specified in section 5 of IEC 62301– 

DD (incorporated by reference; see § 430.3). 

[FR Doc. 2016–25180 Filed 10–19–16; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0578; Directorate 

Identifier 2013–SW–048–AD; Amendment 

39–18684; AD 2016–21–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

(Previously Eurocopter Deutschland 

GmbH) (Airbus Helicopters) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Model MBB–BK 117 C–2 

helicopters with certain duplex trim 

actuators installed. This AD requires 

repetitively inspecting the lateral and 

longitudinal trim actuator output levers 

for correct torque of the nuts. This AD 

was prompted by a design review that 

indicated the attachment screws can 

become loose under certain 

circumstances. These actions are 

intended to prevent the loss of an 

attachment screw, which could result in 

movement of the output lever in an 

axial direction, contact of a bolt 

connecting the control rod to an output 

lever with the actuator housing, and 

subsequent loss of helicopter control. 

DATES: This AD is effective November 

25, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, Inc., 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

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. 

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, the European 

Aviation Safety Agency (EASA) 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 


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72506 Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations 

Operations Office, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Matt 

Wilbanks, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy., Room 6N–321, Fort 

Worth, TX 76177; telephone (817) 222– 

5110; email matt.wilbanks@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On August 18, 2014, at 79 FR 48696, 

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 Airbus Helicopters Model MBB–BK 

117 C–2 helicopters with a lateral 

duplex trim actuator, part number (P/N) 

418–00878–050 or P/N 418–00878–051, 

or a longitudinal duplex trim actuator, 

P/N 418–00878–000 or P/N 418–00878– 

001, installed. The NPRM proposed to 

require repetitively inspecting the 

lateral and longitudinal trim actuator 

output levers for correct torque of the 

nuts. The proposed requirements were 

intended to prevent a loose attachment 

screw, which could result in movement 

of the output lever in an axial direction, 

contact of a bolt connecting the control 

rod to an output lever with the actuator 

housing, and subsequent loss of 

helicopter control. 

The NPRM was prompted by AD No. 

2013–0182, dated August 12, 2013, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for Airbus Helicopters Model 

MBB–BK 117 C–2 helicopters with a 

lateral duplex trim actuator, P/N 418– 

00878–050 or P/N 418–00878–051, or 

with a longitudinal duplex trim 

actuator, P/N 418–00878–000 or P/N 

418–00878–001. EASA advises that 

under unfavorable circumstances, a total 

loss of the trim actuator output lever 

attachment screw could lead to a 

restriction of the lateral and 

longitudinal control range. According to 

EASA, without the attachment screw, 

the output lever can move in the axial 

direction. This condition, if not 

detected, could cause the bolt that 

connects the control rod to the output 

lever to make contact with actuator 

housing, possibly resulting in reduced 

control of the helicopter. 

To prevent this condition, EASA 

requires an initial torque check of the 

lateral and longitudinal trim actuator 

output lever attachment screws, the 

application of a torque marking, and 

repetitive inspections for correct torque 

thereafter. The EASA AD’s requirements 

are considered an interim solution, 

pending a terminating modification. 

Since the issuance of EASA AD No. 

2013–0182, Eurocopter Deutschland 

GmbH has changed its name to Airbus 

Helicopters Deutschland GmbH. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(79 FR 48696, August 18, 2014). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to our bilateral 

agreement with Germany, 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 because Airbus Helicopters is 

currently developing a modification that 

will address the unsafe condition 

identified in this AD. Once this 

modification is developed, approved 

and available, we might consider 

additional rulemaking. 

Related Service Information 

We reviewed Eurocopter (now Airbus 

Helicopters) Alert Service Bulletin 

MBB–BK117 C–2–67A–020, Revision 0, 

dated June 18, 2013 (ASB), which 

advises of a design review that showed 

that a loss of the attachment screw of 

the trim actuator output lever could 

restrict the lateral and longitudinal 

control range. The ASB consequently 

calls for an initial torque check and 

application of torque markings of the 

self-locking nuts, and subsequent 

repetitive inspections to maintain the 

proper torque. 

Costs of Compliance 

We estimate that this AD affects 100 

helicopters of U.S. Registry and that 

labor costs average $85 per work-hour. 

Based on these estimates, we expect the 

following costs: 

• Applying torque and torque 

marking to the lateral and longitudinal 

trim actuator output levers requires 1 

work-hour for a labor cost of $85. No 

parts are needed, so the cost for the U.S. 

fleet totals $8,500. 

• Visually inspecting for correct 

torque requires 0.5 work-hour for a labor 

cost of about $43. No parts are needed, 

so the total cost for the U.S. fleet is 

$4,300 per inspection cycle. 

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 

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, 


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Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations 72507 

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 adding 

the following new airworthiness 

directive (AD): 

2016–21–03 Airbus Helicopters 

Deutschland GmbH (Previously 

Eurocopter Deutschland GmbH) (Airbus 

Helicopters) Helicopters: Amendment 

39–18684; Docket No. FAA–2014–0578; 

Directorate Identifier 2013–SW–048–AD. 

(a) Applicability 

This AD applies to Airbus Helicopters 

Model MBB–BK 117 C–2 helicopters with a 

lateral duplex trim actuator, part number (P/ 

N) 418–00878–050 or P/N 418–00878–051, or 

a longitudinal duplex trim actuator, P/N 418– 

00878–000 or P/N 418–00878–001, installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

loss of a trim actuator output lever 

attachment screw. This condition could 

result in movement of the output lever in an 

axial direction, contact of a bolt connecting 

the control rod to an output lever with the 

actuator housing, and subsequent loss of 

control of the helicopter. 

(c) Effective Date 

This AD becomes effective November 25, 

2016. 

(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) Within 300 hours time-in-service (TIS), 

apply a torque of 31.0 inch-pounds (3.5 Nm) 

to the self-locking nut (nut) on each lateral 

and longitudinal trim actuator output lever 

and apply a torque marking between the nut 

and the screw. 

(2) Thereafter at intervals not to exceed 400 

hours TIS, visually inspect each nut on each 

lateral and longitudinal trim actuator output 

lever to determine whether the torque is at 

31.0 inch-pounds (3.5 Nm). If the torque is 

not at 31.0 inch-pounds, apply a torque of 

31.0 inch-pounds (3.5 Nm), remove the 

previous torque marking, and apply a new 

torque marking between the nut and the 

screw. 

(3) Do not install a lateral duplex trim 

actuator, part number (P/N) 418–00878–050 

or P/N 418–00878–051, or a longitudinal 

duplex trim actuator, P/N 418–00878–000 or 

P/N 418–00878–001, on any helicopter 

unless each nut has been inspected for 

proper torque in accordance with 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 Wilbanks, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

10101 Hillwood Pkwy., Room 6N–321, Fort 

Worth, TX 76177; telephone (817) 222–5110; 

email 9-ASW-FTW-AMOC-Requests@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 

(1) Eurocopter Alert Service Bulletin MBB– 

BK117 C–2–67A–020, Revision 0, dated June 

18, 2013, which is not incorporated by 

reference, contains additional information 

about the subject of this AD. For service 

information identified in this final rule, 

contact Airbus Helicopters, Inc., 2701 N. 

Forum Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232–0323; 

fax (972) 641–3775; or at http://

www.airbushelicopters.com/techpub. You 

may review a copy of the service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Parkway, 

Room 6N–321, Fort Worth, TX 76177. 

(2) The subject of this AD is addressed in 

the European Aviation Agency (EASA) AD 

No. 2013–0182, dated August 12, 2013. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA–2014–0578. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6700, Rotorcraft Flight Control. 

Issued in Fort Worth, Texas, on October 5, 

2016. 

Lance T. Gant, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2016–24860 Filed 10–19–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–5589; Directorate 

Identifier 2014–NM–252–AD; Amendment 

39–18678; AD 2016–20–12] 

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) 2012–20– 

07 for certain Airbus Model A318, 

A319, A320, and A321 series airplanes. 

AD 2012–20–07 required revising the 

Airworthiness Limitations section (ALS) 

of the Instructions for Continued 

Airworthiness (ICA) to incorporate new 

limitations for fuel tank systems, and 

revising the maintenance program to 

incorporate revised fuel maintenance 

and inspection tasks. This new AD 

requires revising the maintenance or 

inspection program to incorporate 

revised fuel airworthiness limitations. 

This AD was prompted by Airbus 

issuing more restrictive maintenance 

requirements and/or airworthiness 

limitations. We are issuing this AD to 

prevent the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, could result 

in a fuel tank explosion and consequent 

loss of the airplane. 

DATES: This AD is effective November 

25, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 25, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of November 21, 2012 (77 FR 

63716, October 17, 2012). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of December 14, 2009 (74 FR 

62219, November 27, 2009). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of August 28, 2007 (72 FR 

40222, July 24, 2007). 

ADDRESSES: For service information 

identified in this final rule, 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.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–2016– 

5589. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 


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