31844 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 

Where: 

E24 = 24-hour energy as determined in 

section 5.10 of this appendix, 

Ebatt = Measured battery energy as determined 

in section 5.8 of this appendix, 

Pm = Maintenance mode power as 

determined in section 5.9 of this 

appendix, 

Psb = Standby mode power as determined in 

section 5.11 of this appendix, 

Poff = Off mode power as determined in 

section 5.12 of this appendix, 

tcd = Charge test duration as determined in 

section 5.2 of this appendix, and 

ta&m, n, tsb, and toff, are constants used 

depending upon a device’s product class 

and found in the following table: 

TABLE 5.3—BATTERY CHARGER USAGE PROFILES

Product class Hours per day *** Charges 

(n) 

Threshold 

charge 

time * 

No. Description 

Rated battery 

energy 

(Ebatt) ** 

Special 

characteristic 

or battery voltage 

Active + 

maintenance 

(ta&m) 

Standby 

(tsb) 

Off 

(toff) Number per 

day Hours 

1 ... Low-Energy ........... ≤5 Wh .................... Inductive Connection ****.20.66 0.10 0.00 0.15 137.73 

2 ... Low-Energy, LowVoltage.<100 Wh ................ <4 V ....................... 7.82 5.29 0.00 0.54 14.48 

3 ... Low-Energy, Medium-Voltage................................. 4–10 V ................... 6.42 0.30 0.00 0.10 64.20 

4 ... Low-Energy, HighVoltage................................. >10 V ..................... 16.84 0.91 0.00 0.50 33.68 

5 ... Medium-Energy, 

Low-Voltage.

100–3000 Wh ........ <20 V ..................... 6.52 1.16 0.00 0.11 59.27 

6 ... Medium-Energy, 

High-Voltage.

................................ ≥20 V ..................... 17.15 6.85 0.00 0.34 50.44 

7 ... High-Energy .......... >3000 Wh .............. ................................ 8.14 7.30 0.00 0.32 25.44 

* If the duration of the charge test (minus 5 hours) as determined in section 5.2 of appendix Y to subpart B of this part exceeds the threshold 

charge time, use equation (ii) to calculate UEC otherwise use equation (i). 

** Ebatt = Rated battery energy as determined in 10 CFR part 429.39(a). 

*** If the total time does not sum to 24 hours per day, the remaining time is allocated to unplugged time, which means there is 0 power consumption and no changes to the UEC calculation needed. 

**** Inductive connection and designed for use in a wet environment (e.g. electric toothbrushes). 

[FR Doc. 2016–11486 Filed 5–19–16; 8:45 a.m.] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0006; Directorate 

Identifier 2013–NM–147–AD; Amendment 

39–18519; AD 2016–10–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A330–200 Freighter, 

A330–200, A330–300, A340–200, A340– 

300, A340–500, and A340–600 series 

airplanes. This AD was prompted by the 

results of endurance qualification tests 

on the trimmable horizontal stabilizer 

actuator (THSA), which revealed a 

partial loss of the no-back brake (NBB) 

efficiency in specific load conditions. 

This AD requires inspecting certain 

THSAs to determine the number of total 

flight cycles the THSA has accumulated, 

and replacing the THSA if necessary. 

We are issuing this AD to detect and 

correct premature wear of the carbon 

friction disks on the NBB of the THSA. 

Such a condition could lead to reduced 

braking efficiency in certain load 

conditions and, in conjunction with the 

inability of the power gear train to keep 

the ball screw in its last commanded 

position, could result in uncommanded 

movements of the trimmable horizontal 

stabilizer (THS) and loss of control of 

the airplane. 

DATES: This AD is effective June 24, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 24, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus SAS, Airworthiness Office— 

EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone 

+33 5 61 93 36 96; fax +33 5 61 93 45 

80; email airworthiness.A330-A340@

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 


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Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 31845 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2014–0006. 

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–2014– 

0006; 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 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 by adding an AD 

that would apply to all Airbus Model 

A330–200 Freighter, A330–200, A330– 

300, A340–200, A340–300, A340–500, 

and A340–600 series airplanes. The 

SNPRM published in the Federal 

Register on December 23, 2015 (80 FR 

79738) (‘‘the SNPRM’’). We preceded 

the SNPRM with a notice of proposed 

rulemaking (NPRM) that published in 

the Federal Register on February 3, 

2014 (79 FR 6104) (‘‘the NPRM’’). The 

NPRM proposed to require inspecting 

certain THSAs to determine the number 

of total flight cycles the THSA has 

accumulated, and replacing the THSA if 

necessary. The NPRM was prompted by 

the results of endurance qualification 

tests on the THSA, which revealed a 

partial loss of the NBB efficiency in 

specific load conditions. The SNPRM 

proposed to revise the NPRM by adding 

airplanes to the proposed applicability, 

reducing the proposed compliance 

times for replacing affected TSHAs, and 

revising the definition of a serviceable 

THSA. We are issuing this AD to detect 

and correct premature wear of the 

carbon friction disks on the NBB of the 

THSA. Such a condition could lead to 

reduced braking efficiency in certain 

load conditions and, in conjunction 

with the inability of the power gear train 

to keep the ball screw in its last 

commanded position, could result in 

uncommanded movements of the THS 

and loss of control of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0257R1, dated May 29, 

2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on all Airbus Model 

A330–200, A330–200 Freighter, A330– 

300, A340–200, and A340–300 series 

airplanes; and Model A340–500 and 

A340–600 series airplanes. The MCAI 

states: 

During endurance qualification tests on 

Trimmable Horizontal Stabilizer Actuator 

(THSA) of another Airbus aeroplane type, a 

partial loss of the no-back brake (NBB) 

efficiency was experienced. Due to THSA 

design similarity on the A330/A340 fleet, a 

similar partial loss of the NBB efficiency was 

identified on THSA Part Number (P/N) 47147 

as installed on A330–300 and A340–200/– 

300 aeroplanes, on THSA P/N 47172 as 

installed on A330–200/–300 and A340–200/ 

–300 aeroplanes, and on THSA P/N 47175 as 

installed on A340–500/600 aeroplanes. 

Investigation results concluded that this 

partial loss of braking efficiency in some 

specific aerodynamic load conditions was 

due to polishing and auto-contamination of 

the NBB carbon friction disks. 

This condition, if not detected and 

corrected and in conjunction with the power 

gear train not able to keep the ball screw in 

its last commanded position, could lead to 

uncommanded movements of the THS, 

possibly resulting in loss of control of the 

aeroplane. 

To address this potential unsafe condition, 

EASA issued AD 2013–0144 [http://

ad.easa.europa.eu/blob/easa_ad_2013_

0144.zip/AD_2013-0144R1_2] to require 

replacement of each THSA that has exceeded 

16,000 flight cycles (FC) in service, to be sent 

in shop for NBB carbon disk replacement. 

Since that AD was issued, a need for 

clarification has been demonstrated, 

regarding the identification of the THSA 

‘affected’ by this requirement. 

For this reason, EASA AD 2013–0144 

[http://ad.easa.europa.eu/blob/easa_ad_

2013_0144.zip/AD_2013-0144R1_2] was 

revised, confirming that this AD only affected 

those THSA identified by Part Number (P/N) 

in Airbus Alert Operator Transmission (AOT) 

A27L005–13. In addition, a note was added 

to make clear that the life limits as specified 

in the current revision of ALS Part 4 are still 

relevant for the affected THSA, as applicable 

to aeroplane model and THSA P/N. 

Since EASA AD 2013–0144R1 [http://

ad.easa.europa.eu/ad/2013-0144R1] was 

issued, further assessment of the ageing/

endurance issue has resulted in the 

conclusion that there is a need to replace the 

NBB installed on the THSA. 

Consequently, EASA issued AD 2014–0257 

[http://ad.easa.europa.eu/blob/EASA_AD_

2014_0257_R1.pdf/AD_2014-0257R1_1] 

which retained the requirements of EASA AD 

2013–0144R1, which was superseded, and 

required removal from service of affected 

THSA. THSA should be sent in shop for NBB 

carbon disk replacement. This [EASA] AD 

affected additional THSA P/Ns when 

compared to EASA AD 2013–0144R1 and 

Airbus AOT A27L005–13. 

Since that [EASA] AD was issued, it was 

determined that it is necessary to consider 

that the THSA removal for NBB disks 

replacement could also be calculated since 

last NBB disk replacement which was done 

in-shop. 

This AD also adds Model A340–541 and 

A340–642 airplanes to the applicability. 

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–2014– 

0006. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information, all dated July 15, 

2014. 

• Service Bulletin A330–27–3199 (for 

Model A330 series airplanes); 

• Service Bulletin A340–27–4190 (for 

Model A340–200 and –300 series 

airplanes); and 

• Service Bulletin A340–27–5062 (for 

Model A340–500 and –600 series 

airplanes). 

The service information describes 

procedures for inspecting the THSA to 

determine the part number and 

replacing THSAs having certain part 

numbers with a new or serviceable part. 

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 94 

airplanes of U.S. registry. 

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31846 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 

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 ........................................................ 3 work-hours × $85 per hour = $255 ............. $0 $255 $23,970 

We estimate the following costs to do 

any necessary replacements that will be 

required based on the results of the 

required inspection. We have no way of 

determining the number of airplanes 

that might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement ................................................................. 23 work-hour × $85 per hour = $1,955 ........................ $722,556 $724,511 

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 adding 

the following new airworthiness 

directive (AD): 

2016–10–08 Airbus: Amendment 39–18519. 

Docket No. FAA–2014–0006; Directorate 

Identifier 2013–NM–147–AD. 

(a) Effective Date 

This AD is effective June 24, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) through (c)(7) of this AD, all 

manufacturer serial numbers. 

(1) Model A330–201, –202, –203, –223, and 

–243 airplanes. 

(2) Model A330–223F and –243F airplanes. 

(3) Model A330–301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes. 

(4) Model A340–211, –212, and –213 

airplanes. 

(5) Model A340–311, –312, and –313 

airplanes. 

(6) Model A340–541 airplanes. 

(7) Model A340–642 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by the results of 

endurance qualification tests on the 

trimmable horizontal stabilizer actuator 

(THSA), which revealed a partial loss of the 

no-back brake (NBB) efficiency in specific 

load conditions. We are issuing this AD to 

detect and correct premature wear of the 

carbon friction disks on the NBB of the 

THSA. Such a condition could lead to 

reduced braking efficiency in certain load 

conditions and, in conjunction with the 

inability of the power gear train to keep the 

ball screw in its last commanded position, 

could result in uncommanded movements of 

the trimmable horizontal stabilizer and loss 

of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection To Determine THSA Part 

Number and Accumulated Total Flight 

Cycles 

Within 90 days after the effective date of 

this AD: Inspect the THSA to determine if it 

has a part number that is specified in 

paragraph (g)(1) or (g)(2) of this AD, and to 

determine the total number of flight cycles 

accumulated since the THSA’s first 

installation on an airplane, or since the most 

recent NBB replacement. A review of 

airplane delivery or maintenance records is 

acceptable in lieu of this inspection if the 

part number of the THSA can be conclusively 

determined from that review. 

(1) For Model A330–200 Freighter, A330– 

200, A330–300, A340–200 and A340–300 

series airplanes: Part number (P/N) 47147– 

500, 47147–700, 47172–300, 47172–500, 

47172–510, or 47172–520. 

(2) For Model A340–500 and –600 series 

airplanes: P/N 47175–200, 47175–300, 

47175–500, or 47175–520. 

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Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 31847 

(h) THSA Replacement for Airbus Model 

A330–200 Freighter, A330–200, A330–300, 

A340–200, and A340–300 Series Airplanes 

For Airbus Model A330–200 Freighter, 

A330–200, A330–300, A340–200, and A340– 

300 series airplanes having a THSA with a 

part number specified in paragraph (g)(1) of 

this AD: At the applicable time specified in 

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

replace each affected THSA with a 

serviceable THSA, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–27–3199, dated July 

15, 2014; or Airbus Service Bulletin A340– 

27–4190, dated July 15, 2014; as applicable. 

Note 1 to paragraphs (h), (i), and (j) of this 

AD: The THSA life limits specified in Part 

4—Aging System Maintenance of the Airbus 

A330 and A340 Airworthiness Limitations 

Sections are still relevant, as applicable to 

airplane model and THSA part number. 

(1) For a THSA that has accumulated or 

exceeded 20,000 total flight cycles since the 

THSA’s first installation on an airplane, or 

since the most recent NBB replacement, 

whichever is later, as of the effective date of 

this AD: Within 6 months after the effective 

date of this AD. 

(2) For a THSA that has accumulated or 

exceeded 16,000 total flight cycles, but less 

than 20,000 total flight cycles since the 

THSA’s first installation on an airplane, or 

since the most recent NBB replacement, 

whichever is later, as of the effective date of 

this AD: At the applicable time specified in 

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

(i) For Model A330–200 Freighter, A330– 

200, and A330–300 series airplanes: Within 

12 months after the effective date of this AD 

but without exceeding 20,000 total flight 

cycles. 

(ii) For Model A340–200, and A340–300 

series airplanes: Within 12 months after the 

effective date of this AD but without 

exceeding 20,000 total flight cycles. 

(3) For a THSA that has accumulated less 

than 16,000 total flight cycles since first 

installation on an airplane, or since the most 

recent NBB replacement, whichever is later, 

as of the effective date of this AD: At the 

applicable time specified in paragraph (i) of 

this AD. 

(i) Replacement Times for Airbus Model 

A330–200 Freighter, A330–200, A330–300, 

A340–200, and A340–300 Series Airplanes 

With THSAs Having Less Than 16,000 Total 

Flight Cycles as of the Effective Date of This 

AD 

The requirements of this paragraph apply 

to Airbus Model A330–200 Freighter, A330– 

200, A330–300, A340–200, and A340–300 

series airplanes having a THSA with a part 

number specified in paragraph (g)(1) of this 

AD that has accumulated less than 16,000 

total flight cycles since first installation on an 

airplane, or since the most recent NBB 

replacement, whichever is later, as of the 

effective date of this AD. Not later than the 

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

(i)(3) of this AD, as applicable: For any THSA 

having reached or exceeded on that date the 

corresponding number of total flight cycles as 

specified in paragraphs (i)(1), (i)(2), and (i)(3) 

of this AD, as applicable, replace the THSA 

with a serviceable unit, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A330–27–3199, dated July 

15, 2014; or Airbus Service Bulletin A340– 

27–4190, dated July 15, 2014; as applicable. 

(1) As of 12 months after the effective date 

of this AD: The THSA flight-cycle limit 

(since first installation on an airplane, or 

since last NBB replacement, whichever 

occurs later) is 16,000 total flight cycles. 

(2) As of July 31, 2017: The THSA flightcycle limit (since first installation on an 

airplane, or since last NBB replacement, 

whichever occurs later) is 14,000 total flight 

cycles. 

(3) As of July 31, 2018: The THSA flightcycle limit (since first installation on an 

airplane, or since last NBB replacement, 

whichever occurs later) is 12,000 total flight 

cycles. 

(j) THSA Replacement for Airbus Model 

A340–500 and –600 Series Airplanes 

For Airbus Model A340–500 and A340– 

600 series airplanes having a THSA with a 

part number specified in paragraph (g)(2) of 

this AD: Not later than the date specified in 

paragraphs (j)(1), (j)(2), (j)(3), and (j)(4) of this 

AD, as applicable, for any THSA having 

reached or exceeded on that date the 

corresponding number of total flight cycles as 

specified in paragraphs (j)(1), (j)(2), (j)(3), and 

(j)(4) of this AD, as applicable, replace each 

affected THSA with a serviceable THSA, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A340– 

27–5062, dated July 15, 2014. 

(1) As of the effective date of this AD: The 

THSA flight-cycle limit (since first 

installation on an airplane, or since last NBB 

replacement, whichever occurs later) is 6,000 

total flight cycles. 

(2) As of April 30, 2017: The THSA flightcycle limit (since first installation on an 

airplane, or since last NBB replacement, 

whichever occurs later) is 5,200 total flight 

cycles. 

(3) As of April 30, 2018: The THSA flightcycle limit (since first installation on an 

airplane, or since last NBB replacement, 

whichever occurs later) is 4,400 total flight 

cycles. 

(4) As of April 30, 2019: The THSA flightcycle limit (since first installation on an 

airplane, or since last NBB replacement, 

whichever occurs later) is 3,500 total flight 

cycles. 

(k) THSA Replacement Intervals for All 

Airbus Airplanes Identified in Paragraph (c) 

of This AD 

For any part installed, as required by this 

AD, having a part number identified in 

paragraph (g)(1) or (g)(2) of this AD: From the 

dates specified in paragraphs (i) and (j) of 

this AD, as applicable, and prior to exceeding 

the accumulated number of total flight cycles 

corresponding to each time, replace each 

affected THSA with a serviceable part, in 

accordance with the Accomplishment 

Instructions of the applicable service 

information identified in paragraphs (k)(1), 

(k)(2), and (k)(3) of this AD. 

(1) Airbus Service Bulletin A330–27–3199, 

dated July 15, 2014. 

(2) Airbus Service Bulletin A340–27–4190, 

dated July 15, 2014. 

(3) Airbus Service Bulletin A340–27–5062, 

dated July 15, 2014. 

(l) Definition of Serviceable THSA 

For the purposes of this AD, a serviceable 

THSA is a THSA: 

(1) Having a part number identified in 

paragraph (g)(1) or (g)(2) of this AD that has 

not exceeded any of the total accumulated 

flight cycles identified in paragraphs (i)(1) 

through (i)(3) of this AD, or paragraphs (j)(1) 

through (j)(4) of this AD, as applicable; or 

(2) Having a part number that is not 

identified in paragraph (g)(1) or (g)(2) of this 

AD. 

(m) Parts Installation Limitation 

From each date specified in paragraphs 

(i)(1), (i)(2), and (i)(3) of this AD, and 

paragraphs (j)(1) through (j)(4) of this AD, as 

applicable, a THSA having a part number 

identified in paragraph (g)(1) or (g)(2) of this 

AD may be installed on any airplane, 

provided the THSA has not exceeded the 

corresponding number of accumulated total 

flight cycles. 

(n) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; 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: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

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31848 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(o) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0257R1, dated 

May 29, 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– 

2014–0006. 

(p) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A330-27–3199, 

dated July 15, 2014. 

(ii) Airbus Service Bulletin A340–27–4190, 

dated July 15, 2014. 

(iii) Airbus Service Bulletin A340–27– 

5062, dated July 15, 2014. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@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 May 9, 

2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–11575 Filed 5–19–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–6548; Directorate 

Identifier 2015–NM–114–AD; Amendment 

39–18520; AD 2016–10–09] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 787–8 and 

787–9 airplanes equipped with General 

Electric engines. This AD was prompted 

by reports of cracking in barrel nuts on 

a forward engine mount of Model 747– 

8 airplanes, which shares a similar 

design to the forward engine mount of 

Model 787–8 and 787–9 airplanes. This 

AD requires, for certain airplanes, 

replacement of the four barrel nuts of 

the forward engine mount on each 

engine. For certain other airplanes, this 

AD requires an inspection to determine 

if any forward engine mount barrel nut 

having a certain part number is 

installed; and related investigative and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

cracking of the forward engine mount 

barrel nuts. Such cracking could result 

in reduced load capacity of the forward 

engine mount and could result in 

separation of an engine from the 

airplane and consequent loss of control 

of the airplane. 

DATES: This AD is effective June 24, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 24, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Data & Services Management, 

P.O. Box 3707, MC 2H–65, Seattle, WA 

98124–2207; telephone: 206–544–5000, 

extension 1; fax: 206–766–5680; Internet 

https://www.myboeingfleet.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– 

6548. 

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– 

6548; 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 (phone: 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: 

Allen Rauschendorfer, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

Seattle Aircraft Certification Office, 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6487; 

fax: 425–917–6590; email: 

allen.rauschendorfer@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 787–8 and 787–9 airplanes 

equipped with General Electric engines. 

The NPRM published in the Federal 

Register on December 11, 2015 (80 FR 

76878) (‘‘the NPRM’’). The NPRM was 

prompted by reports of cracking in 

barrel nuts on a forward engine mount 

of Model 747–8 airplanes, which shares 

a similar design to the forward engine 

mount of Model 787–8 and 787–9 

airplanes. The NPRM proposed to 

require, for certain airplanes, 

replacement of the four barrel nuts of 

the forward engine mount on each 

engine. For certain other airplanes, the 

NPRM proposed to require an 

inspection to determine if any forward 

engine mount barrel nut having a 

certain part number is installed; and 

related investigative and corrective 

actions if necessary. We are issuing this 

AD to detect and correct cracking of the 

forward engine mount barrel nuts. Such 

cracking could result in reduced load 

capacity of the forward engine mount 

and could result in separation of an 

engine from the airplane and 

consequent loss of control of the 

airplane. 

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 Revise the Compliance 

Time 

United Airlines requested that the 

compliance time in the NPRM for Group 

1 airplanes be changed from 2 years to 

‘‘at next engine change.’’ United 

considered the proposed compliance 

time to be ‘‘expedited’’ because it took 

Boeing 7 months to publish the service 

information operators would be 

required to use to comply with the 

requirements in the NPRM, and it took 

mstockstill on DSK5VPTVN1PROD with RULES