47696 Federal Register / Vol. 81, No. 141 / Friday, July 22, 2016 / Rules and Regulations 

correct the unsafe condition on these 

products. 

(f) Compliance 

Comply with paragraphs (g)(1) through (2) 

of this AD using the following service 

bulletins within the compliance times 

specified below, unless already done: 

(1) For Models SA26–T and SA26–AT: M7 

Aerospace LLC Service Bulletin (SB) 26–27– 

002, dated October 8, 2015; 

(2) For Models SA226–AT, SA226–T, 

SA226–T(B), and SA226–TC: M7 Aerospace 

LLC SB 226–27–078, dated October 8, 2015; 

(3) For Models SA227–AC(C–26A), SA227– 

AT, SA227–BC(C–26A), and SA227–TT: M7 

Aerospace LLC SB 227–27–058, dated 

October 8, 2015; or 

(4) For Models SA227–CC and SA227–DC 

(C–26B): M7 Aerospace LLC SB CC7–27–030, 

dated October 8, 2015. 

(g) Actions 

(1) For all airplanes: Within the next 2,000 

hours time-in-service (TIS) after [insert date 

35 days after date of publication in the 

Federal Register] (the effective date of this 

AD) or no later than when the airplane 

accumulates 20,000 hours TIS, whichever 

occurs later, do an initial inspection of the 

cockpit control column horizontal tube for 

cracks following the Accomplishment 

Instructions in section 2. of the service 

bulletins identified in paragraphs (f)(1), (2), 

(3), or (4) of this AD, as applicable; and 

repetitively inspect as follows: 

(i) For airplanes with less than 35,000 

hours TIS as of [insert date 35 days after date 

of publication in the Federal Register] (the 

effective date of this AD): Repetitively 

inspect the cockpit control column 

horizontal tube for cracks every 5,000 hours 

TIS until the airplane reaches 35,000 hours 

TIS at which time do the inspection within 

2,000 hours TIS from the last inspection or 

within the next 100 hours TIS, whichever 

occurs later, and then thereafter at intervals 

not to exceed 2,000 hours TIS. 

(ii) For airplanes with 35,000 hours TIS or 

more as of [insert date 35 days after date of 

publication in the Federal Register] (the 

effective date of this AD): Repetitively 

inspect the cockpit control column 

horizontal tube for cracks every 2,000 hours 

TIS. 

(2) For all airplanes: If any cracks are 

found following the inspections required in 

paragraphs (g)(1), (g)(1)(i), or (ii), as 

applicable, before further flight, repair the 

control column following the 

Accomplishment Instructions in section 2. of 

the service bulletins identified in paragraphs 

(f)(1), (2), (3), or (4), as applicable, of this AD. 

Note to paragraph (g)(1) through (2) of this 

AD: The reporting of information requested 

in paragraph 2.H. of the Accomplishment 

Instructions in the service bulletins 

identified in paragraphs (f)(1), (2), (3), and (4) 

of this AD is not a required action of this AD. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Fort Worth Airplane 

Certification Office, 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (j) of this AD. 

(2) 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. 

(i) Related Information 

For more information about this AD, 

contact Andrew McAnaul, Aerospace 

Engineer, FAA, ASW–143 (c/o San Antonio 

MIDO), 10100 Reunion Place, Suite 650, San 

Antonio, Texas 78216; phone: (210) 308– 

3365; fax: (210) 308–3370; email: 

andrew.mcanaul@faa.gov. 

(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) M7 Aerospace LLC Service Bulletin (SB) 

26–27–002, dated October 8, 2015; 

(ii) M7 Aerospace LLC SB 226–27–078, 

dated October 8, 2015; 

(iii) M7 Aerospace LLC SB 227–27–058, 

dated October 8, 2015; or 

(iv) M7 Aerospace LLC SB CC7–27–030, 

dated October 8, 2015. 

(3) For service information identified in 

this AD, contact M7 Aerospace LLC, 10823 

NE Entrance Road, San Antonio, Texas 

78216; phone: (210) 824–9421; fax: (210) 

804–7766; Internet: http://www.elbitsystemsus.com; email: MetroTech@

M7Aerospace.com. 

(4) You may view this referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, call 

816–329–4148. 

(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 Kansas City, Missouri, on July 13, 

2016. 

Pat Mullen, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–17039 Filed 7–21–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–3993; Directorate 

Identifier 2015–NM–065–AD; Amendment 

39–18592; AD 2016–15–01] 

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 A300 series airplanes; 

Model A300 B4–600, B4–600R, F4–600R 

series airplanes, and Model A300 C4– 

605R Variant F airplanes (collectively 

called Model A300–600 series 

airplanes); and Model A310 series 

airplanes. This AD was prompted by 

reports of partial loss of no-back brake 

(NBB) efficiency on the trimmable 

horizontal stabilizer actuator (THSA). 

This AD requires an inspection to 

determine THSA part numbers, serial 

numbers, and flight cycles on certain 

THSAs; and repetitive replacement of 

certain THSAs. We are issuing this AD 

to prevent loss of THSA NBB efficiency, 

which, in conjunction with the inability 

of the power gear to keep the ball screw 

in its last commanded position, could 

lead to an uncommanded movement of 

the horizontal stabilizer, possibly 

resulting in loss of control of the 

airplane. 

DATES: This AD is effective August 26, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 26, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus SAS, Airworthiness Office— 

EAW, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; 

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

5 61 93 44 51; email: account.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 No. 

FAA–2016–3993. 


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Federal Register / Vol. 81, No. 141 / Friday, July 22, 2016 / Rules and Regulations 47697 

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–2016– 

3993; 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone: 425–227–2125; 

fax: 425–227–1149. 

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 all Airbus Model A300 series 

airplanes; Model A300 B4–600, B4– 

600R, F4–600R series airplanes, and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes); and Model 

A310 series airplanes. The NPRM 

published in the Federal Register on 

March 7, 2016 (81 FR 11690) (‘‘the 

NPRM’’). The NPRM was prompted by 

reports of partial loss of NBB efficiency 

on the THSA. The NPRM proposed to 

require an inspection to determine 

THSA part numbers, serial numbers, 

and flight cycles on certain THSAs; and 

repetitive replacement for certain 

THSAs. We are issuing this AD to 

prevent loss of THSA NBB efficiency, 

which, in conjunction with the inability 

of the power gear to keep the ball screw 

in its last commanded position, could 

lead to an uncommanded movement of 

the horizontal stabilizer, possibly 

resulting in 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 AD 2015–0081, 

dated May 7, 2015 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

on all Airbus Model A300 series 

airplanes; Model A300 B4–600, B4– 

600R, F4–600R series airplanes, and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes); and Model 

A310 series airplanes. The MCAI states: 

During endurance qualification tests on a 

Trimmable Horizontal Stabilizer Actuator 

(THSA) concerning another aeroplane type, a 

partial loss of the no-back brake (NBB) 

efficiency was experienced. 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. 

Due to design similarity on the A300–600, 

A300–600ST and A310 fleet, the same tests 

were initiated by the THSA manufacturer on 

certain type THSA, sampled from the field. 

Subject tests confirmed that THSA Part 

Number (P/N) 47142 series, as installed on 

the A300–600, A300–600ST and A310 fleet, 

are also affected by this partial loss of NBB 

efficiency. 

This condition, if not detected and 

corrected, and in conjunction with the power 

gear not able to keep the ball screw in its last 

commanded position, could potentially lead 

to an uncommanded movement of the 

Horizontal Stabilizer, possibly resulting in 

loss of control of the aeroplane. 

For the reasons described above, this 

[EASA] AD requires the removal from service 

of each affected THSA, with the intent of inshop NBB carbon disk replacement. 

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–2016– 

3993. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Support for the NPRM 

The Airline Pilots Association 

International stated that it fully supports 

the intent of the NPRM. 

Requests To Revise Compliance Date 

Airbus, FedEx Express, and United 

Parcel Service requested that we revise 

the compliance date in paragraph (j)(3) 

of the proposed AD from February 1, 

2018, to February 1, 2019. The 

commenters stated that this revision 

would match the MCAI. 

We agree with the commenters’ 

request. This was a typographical error. 

Our intent was to match the MCAI. We 

have revised paragraph (j)(3) of this AD 

accordingly. 

Request To Allow Maintenance Records 

Review 

FedEx Express requested that we 

allow a review of the operator’s 

maintenance records to determine the 

part number and serial number of the 

THSA specified in paragraph (h)(1) of 

the proposed AD. FedEx Express stated 

that this review would accomplish the 

same intent as a physical inspection of 

the THSA. 

We agree with the commenter’s 

request. We have revised paragraph 

(h)(1) of this AD to allow doing a review 

of airplane maintenance records in lieu 

of the THSA inspection if the part 

number and serial number of the THSA 

can be conclusively determined from 

that review. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We 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 Airbus Service 

Bulletin A300–27–6070, dated February 

17, 2015; and Airbus Service Bulletin 

A310–27–2106, dated February 17, 

2015. This service information describes 

procedures for inspection and 

replacement of the THSA. 

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 152 

airplanes of U.S. registry. 

We also estimate that it would take 

about 27 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts would 

cost about $590,000 per product. Based 

on these figures, we estimate the cost of 

this AD on U.S. operators to be 

$90,028,840, or $592,295 per product. 

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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47698 Federal Register / Vol. 81, No. 141 / Friday, July 22, 2016 / Rules and Regulations 

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): 

2016–15–01 Airbus: Amendment 39–18592. 

Docket No. FAA–2016–3993; Directorate 

Identifier 2015–NM–065–AD. 

(a) Effective Date 

This AD is effective August 26, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1) through (c)(6) 

of this AD, certificated in any category, all 

manufacturer serial numbers. 

(1) Airbus Model A300 B2–1A, B2–1C, 

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

203 airplanes. 

(2) Airbus Model A300 B4–601, B4–603, 

B4–620, and B4–622 airplanes. 

(3) Airbus Model A300 B4–605R and B4– 

622R airplanes. 

(4) Airbus Model A300 F4–605R and F4– 

622R airplanes. 

(5) Airbus Model A300 C4–605R Variant F 

airplanes. 

(6) Airbus Model A310–203, –204, –221, 

–222, –304, –322, –324, and –325 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by reports of partial 

loss of no-back brake (NBB) efficiency on the 

trimmable horizontal stabilizer actuator 

(THSA). We are issuing this AD to prevent 

loss of THSA NBB efficiency, which, in 

conjunction with the inability of the power 

gear to keep the ball screw in its last 

commanded position, could lead to an 

uncommanded movement of the horizontal 

stabilizer, possibly resulting in loss of control 

of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Affected THSAs 

THSAs affected by the requirements of this 

AD have part numbers (P/Ns) 47142–403, 

47142–413, 47142–414, and 47142–423. 

Note 1 to paragraph (g) of this AD: FAA 

AD 2011–15–08, Amendment 39–16755 (76 

FR 42029, July 18, 2011), requires installation 

of three secondary retention plates for the 

gimbal bearings on the THSA upper primary 

attachment, which involved a THSA part 

number change from the –300 series to the 

–400 series. 

Note 2 to paragraph (g) of this AD: The life 

limits specified in Part 4 of the airworthiness 

limitations section are still relevant for the 

affected THSA. This AD addresses a 

replacement limit for the NBB disks installed 

on the THSA, not the life limit for the THSA 

itself. 

(h) Inspection for Affected THSAs, Flight 

Cycles, and THSA Replacement 

Before each date and before exceeding the 

corresponding THSA flight-cycle limits 

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

of this AD, do the actions specified in 

paragraphs (h)(1) and (h)(2) of this AD; and 

before exceeding the flight-cycle limit 

corresponding to each date as specified in 

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

do the actions specified in paragraph (i) of 

this AD. 

(1) Do an inspection of the THSA to 

determine the part number and serial 

number. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the part number and serial 

number of the THSA can be conclusively 

determined from that review. 

(2) Do an inspection of the airplane 

maintenance records to determine the flight 

cycles accumulated on each affected THSA 

since first installation on an airplane, or 

since last NBB replacement, whichever is 

later. If no maintenance records conclusively 

identifying the last NBB disk replacement are 

available, the flight cycles accumulated since 

first installation of the THSA on an airplane 

apply. 

(i) THSA Replacement 

By each date specified in paragraphs (j)(1), 

(j)(2), and (j)(3) of this AD, for those affected 

THSAs having reached or exceeded the 

corresponding number of flight cycles 

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

of this AD, replace the THSA with a 

serviceable unit, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–27–6070, dated 

February 17, 2015; or Airbus Service Bulletin 

A310–27–2106, dated February 17, 2015, as 

applicable. 

(j) Compliance Dates and THSA Flight-Cycle 

Limits 

Paragraphs (j)(1), (j)(2), and (j)(3) of this AD 

specify compliance dates and THSA flightcycle limits for accomplishing the actions 

required by paragraphs (h) and (i) of this AD. 

(1) As of 30 days after the effective date of 

this AD: The affected THSA flight-cycle limit 

is 30,000 flight cycles since first installation 

of the THSA on an airplane, or since last 

NBB replacement, whichever is later. 

(2) As of February 1, 2017: The affected 

THSA flight-cycle limit is 20,000 flight cycles 

since first installation of the THSA on an 

airplane, or since last NBB replacement, 

whichever is later. 

(3) As of February 1, 2019: The affected 

THSA flight-cycle limit is 14,600 flight cycles 

since first installation of the THSA on an 

airplane, or since last NBB replacement, 

whichever is later. 

(k) Serviceable THSA Definition 

For the purpose of this AD, a serviceable 

THSA is a unit identified in paragraph (k)(1) 

or (k)(2) of this AD. 

(1) A THSA identified in paragraph (g) of 

this AD that, as of each date specified in 

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

has not exceeded the flight-cycle limits 

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

of this AD since first installation of the THSA 

on an airplane, or since the last NBB disk 

replacement, whichever is later. 

(2) A THSA with a different part number 

(e.g., a THSA that is not identified in 

paragraph (g) of this AD) that is not affected 

by the requirements of this AD. 

(l) THSA Replacements 

As of each date and before exceeding the 

flight-cycle limit corresponding to each date 


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Federal Register / Vol. 81, No. 141 / Friday, July 22, 2016 / Rules and Regulations 47699 

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

of this AD: Replace each affected THSA with 

a serviceable unit, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–27–6070, dated 

February 17, 2015; or Airbus Service Bulletin 

A310–27–2106, dated February 17, 2015. 

(m) Parts Installation Limitation 

Before each date specified in paragraphs 

(j)(1), (j)(2), and (j)(3) of this AD, an operator 

may install an affected THSA on an airplane, 

provided that the unit has not exceeded the 

corresponding number of flight cycles 

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

of this AD, since first installation on an 

airplane, or since last NBB replacement, 

whichever is later. 

(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 Dan 

Rodina, Aerospace Engineer, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone: 425– 

227–2125; fax: 425–227–1149. Information 

may be emailed to: 9-ANM-116-AMOCREQUESTS@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 

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 AD 

2015–0081, dated May 7, 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–2016–3993. 

(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 A300–27–6070, 

dated February 17, 2015. 

(ii) Airbus Service Bulletin A310–27–2106, 

dated February 17, 2015. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

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

93 44 51; email: account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on July 11, 

2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–17014 Filed 7–21–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 91 

[Docket No.: FAA–2014–0225; Amdt. No. 

91–331C] 

RIN 2120–AK78 

Extension of the Prohibition Against 

Certain Flights in the Simferopol 

(UKFV) and Dnipropetrovsk (UKDV) 

Flight Information Regions (FIRs); 

Technical Amendment 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; technical 

amendment. 

SUMMARY: On October 27, 2015, the 

Federal Aviation Administration (FAA) 

published a final rule extending the 

prohibition against certain flight 

operations in the Simferopol (UKFV) 

and Dnipropetrovsk (UKDV) flight 

information regions (FIRs) by all United 

States (U.S.) air carriers; U.S. 

commercial operators; persons 

exercising the privileges of a U.S. 

airman certificate, except when such 

persons are operating a U.S.-registered 

aircraft for a foreign air carrier; and 

operators of U.S.-registered civil aircraft, 

except when such operators are foreign 

air carriers. The State Aviation 

Administration of Ukraine conducted 

and completed an airspace restructuring 

that altered the Simferopol (UKFV) and 

Dnipropetrovsk (UKDV) Flight 

Information Region (FIR) altitude 

structure specified in the final rule. To 

address the Ukraine airspace 

restructuring and provide additional 

clarity, this technical amendment 

specifically identifies the prohibited 

airspace in which Special Federal 

Aviation Regulation (SFAR) 113, 

applies, with inclusive altitudes and 

lateral limitations (latitude and 

longitude coordinates). 

DATES: This final rule is effective on July 

21, 2016. 

FOR FURTHER INFORMATION CONTACT: 

Michael Filippell, Air Transportation 

Division, AFS–220, Flight Standards 

Service, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC 20591; 

telephone: 202–267–8166; email: 

michael.e.filippell@faa.gov. 

SUPPLEMENTARY INFORMATION: 

I. Good Cause for Immediate Adoption 

Section 553(b)(3)(B) of the 

Administrative Procedure Act (APA) (5 

U.S.C.) authorizes agencies to dispense 

with notice and comment procedures 

for rules when the agency for ‘‘good 

cause’’ finds that those procedures are 

‘‘impracticable, unnecessary, or contrary 

to the public interest.’’ Under this 

section, an agency, upon finding good 

cause, may issue a final rule without 

seeking comment prior to the 

rulemaking. 

The FAA finds that good cause exists 

under APA section 553(b)(3)(B) for this 

technical amendment to published 

without public notice and comment 

because this amendment is limited to 

providing additional clarity concerning 

specific airspace subject to the existing 

SFAR restriction, by adding latitude and 

longitude coordinates in lieu of the 

names for the FIRs. 

In addition, section 553(d)(3) of the 

Administrative Procedure Act requires 

publication of a substantive rule must 

be made not less than 30 days before the 

effective date except when the agency 


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