41878 Federal Register / Vol. 82, No. 170 / Tuesday, September 5, 2017 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9521; Product 

Identifier 2016–NM–061–AD; Amendment 

39–19018; AD 2017–18–09] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Defense and Space S.A. (Formerly 

Known as Construcciones 

Aeronauticas, S.A.) 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 Defense and Space S.A. Model 

CN–235, CN–235–100, CN–235–200, 

CN–235–300, and C–295 airplanes. This 

AD was prompted by reports of 

excessive play between bushings and 

their respective fitting housings at 

certain elevator fittings. This AD 

requires a one-time detailed inspection 

and repetitive eddy current inspections 

of the elevator hinge fitting and bracket 

assembly, and corrective actions if 

necessary. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective October 10, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 10, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Defense and Space, Services/ 

Engineering Support, Avenida de 

Arago ́n 404, 28022 Madrid, Spain; fax 

+34 91 585 31 27; email 

MTA.TechnicalService@airbus.com. 

You may view this referenced service 

information at the FAA, Transport 

Standards Branch, 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– 

9521. 

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– 

9521; 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: 

Shahram Daneshmandi, Aerospace 

Engineer, International Section, 

Transport Standards Branch, FAA, 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; telephone: 425–227–1112; 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 Defense and Space 

S.A. Model CN–235, CN–235–100, CN– 

235–200, CN–235–300, and C–295 

airplanes. The NPRM published in the 

Federal Register on January 5, 2017 (82 

FR 1269) (‘‘the NPRM’’). The NPRM was 

prompted by reports of excessive play 

between bushings and their respective 

fitting housings at certain elevator 

fittings. The NPRM proposed to require 

a one-time detailed inspection and 

repetitive eddy current inspections of 

the elevator hinge fitting and bracket 

assembly, and corrective actions if 

necessary. We are issuing this AD to 

prevent excessive play between 

bushings and their respective fitting 

housings, which could lead to failure or 

detachment of any of the affected 

structural parts, with a possible result of 

reduced 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 2016–0075, 

dated April 19, 2016 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus Defense and Space S.A. 

Model CN–235, CN–235–100, CN–235– 

200, CN–235–300, and C–295 airplanes. 

The MCAI states: 

Excessive play between bushings and their 

respective fitting housing was reported at 

Stabilizer Station (STA) 4850, affecting the 

outboard and inboard elevator hinge fittings 

and attachment fittings; and the horizontal 

stabilizer elevator linkage. Additionally, 

excessive misalignment was detected 

between the elevator hinge fittings and the 

elevator brackets during further analysis of 

the reported cases. Furthermore, an 

occurrence of an elevator hinge fitting crack 

was reported. 

This condition, if not detected and 

corrected, could lead to failure or detachment 

of any of the affected structural parts, 

possibly resulting in reduced control of the 

aeroplane. 

To address this potentially unsafe 

condition, Airbus Defence & Space (D&S) 

issued Alert Operator Transmissions (AOT) 

AOT–CN235–55–0001 Revision 2 and AOT– 

C295–55–0001 Revision 2 to provide 

inspection instructions to detect 

misalignment between the elevator hinge 

fittings and the elevator brackets. 

Additionally, Airbus D&S issued AOT– 

CN235–55–0003 and AOT–C295–55–0003 to 

provide inspection instructions to detect 

cracking of elevator hinge fitting and 

attachment fitting. 

For the reasons described above, this 

[EASA] AD requires a one-time [detailed] 

inspection of the elevator hinge fittings and 

the elevator brackets, repetitive [eddy 

current] inspections of elevator hinge fittings 

and attachment fittings, and depending on 

findings, accomplishment of applicable 

corrective action(s) [e.g. repair(s)]. 

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– 

9521. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM 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 NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

Airbus Defense and Space S.A. has 

issued the following Alert Operators 

Transmissions (AOT). 

• Airbus Defense and Space S.A. 

AOT AOT–CN235–55–0001, Revision 2, 

dated March 10, 2015. The service 

information describes procedures for a 

detailed visual inspection of the 

elevator hinge fitting and bracket 

assembly to detect excessive play 

between bushings and their respective 

fitting housings, and to detect cracks; 

and corrective actions if necessary. 

• Airbus Defense and Space S.A. 

AOT AOT–CN235–55–0003, dated 

December 22, 2015. The service 

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Federal Register / Vol. 82, No. 170 / Tuesday, September 5, 2017 / Rules and Regulations 41879 

information describes procedures for 

repetitive eddy current inspections to 

detect cracks in the elevator hinge 

fitting and bracket assembly, and 

corrective actions if necessary. 

• Airbus Defense and Space S.A. 

AOT AOT–C295–55–0001, Revision 2, 

dated April 9, 2015. The service 

information describes procedures for a 

detailed visual inspection of the 

elevator hinge fitting and bracket 

assembly to detect excessive play 

between bushings and their respective 

fitting housings, and to detect cracks; 

and corrective actions if necessary. 

• Airbus Defense and Space S.A. 

AOT AOT–C295–55–0003, dated 

December 22, 2015. The service 

information describes procedures for 

repetitive eddy current inspections to 

detect cracks in the elevator hinge 

fitting and bracket assembly, and 

corrective actions if necessary. 

These documents are distinct since 

they apply to different airplane models 

in different configurations. 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 14 

airplanes of U.S. registry. 

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 .......................... 2 work-hours × $85 per hour = $170 

per inspection cycle.

$0 $170 per inspection cycle ..... $2,380 per inspection cycle. 

We estimate the following costs to do 

any necessary repairs that will be 

required based on the results of the 

inspection. We have no way of 

determining the number of airplanes 

that might need this repair: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Repair ........................................................................... 45 work-hours × $85 per hour = $3,825 ...................... $10,000 $13,825 

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. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to transport category 

airplanes to the Director of the System 

Oversight Division. 

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): 

2017–18–09 Airbus Defense and Space S.A. 

(Formerly Known as Construcciones 

Aeronauticas, S.A.): Amendment 39– 

19018; Docket No. FAA–2016–9521; 

Product Identifier 2016–NM–061–AD. 

(a) Effective Date 

This AD is effective October 10, 2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Defense and 

Space S.A. (formerly known as 

Construcciones Aeronauticas, S.A.) Model 

CN–235, CN–235–100, CN–235–200, CN– 

235–300, and C–295 airplanes, certificated in 

any category, all manufacturer serial 

numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55, Stabilizers. 

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41880 Federal Register / Vol. 82, No. 170 / Tuesday, September 5, 2017 / Rules and Regulations 

(e) Reason 

This AD was prompted by reports of 

excessive play between bushings and their 

respective fitting housings at certain elevator 

fittings. We are issuing this AD to prevent 

excessive play between bushings and their 

respective fitting housings, which could lead 

to failure or detachment of any of the affected 

structural parts, with a possible result of 

reduced control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) One-Time Detailed Visual Inspection 

Before exceeding 600 flight hours since 

first flight of the airplane, or within 300 flight 

hours after the effective date of this AD, 

whichever occurs later, but not before 

exceeding 300 flight hours since first flight of 

the airplane: Do a detailed visual inspection 

of the elevator hinge fitting and bracket 

assembly to detect excessive play between 

bushings and their respective fitting 

housings, and to detect cracks, in accordance 

with the instructions of Airbus Defense and 

Space S.A. Alert Operators Transmission 

(AOT) AOT–CN235–55–0001, Revision 2, 

dated March 10, 2015; or AOT AOT–C295– 

55–0001, Revision 2, dated April 9, 2015; as 

applicable. 

(h) Corrective Action for Discrepancies 

Found During Detailed Visual Inspection 

If, during the inspection required by 

paragraph (g) of this AD, any discrepancy is 

detected, as defined in the instructions of 

Airbus Defense and Space S.A. AOT AOT– 

CN235–55–0001, Revision 2, dated March 10, 

2015; or AOT AOT–C295–55–0001 Revision 

2, dated April 9, 2015; as applicable: Before 

further flight, accomplish applicable 

corrective actions, in accordance with the 

instructions of Airbus Defense and Space 

S.A. AOT AOT–CN235–55–0001, Revision 2, 

dated March 10, 2015; or AOT AOT–C295– 

55–0001, Revision 2, dated April 9, 2015; as 

applicable. Where Airbus Defense and Space 

S.A. AOT AOT–CN235–55–0001, Revision 2, 

dated March 10, 2015; or AOT AOT–C295– 

55–0001 Revision 2, dated April 9, 2015; 

specifies to contact Airbus Defense and 

Space S.A. for corrective actions, before 

further flight, accomplish corrective actions 

in accordance with the procedures specified 

in paragraph (n)(2) of this AD. 

(i) Repetitive Eddy Current Inspections— 

Model CN–235, CN–235–100, CN–235–200, 

and CN–235–300 Airplanes 

For Model CN–235, CN–235–100, CN–235– 

200, and CN–235–300 airplanes: Do the 

actions required by paragraphs (i)(1) and 

(i)(2) of this AD. 

(1) Within the applicable compliance time 

specified in table 1 to paragraph (i)(1) of this 

AD: Do an eddy current inspection to detect 

cracks in the elevator hinge fitting and 

bracket assembly, in accordance with the 

instructions of Airbus Defense and Space 

S.A. AOT AOT–CN235–55–0003, dated 

December 22, 2015. 

TABLE 1 TO PARAGRAPH (i)(1) OF THIS AD—INITIAL COMPLIANCE TIMES FOR MODEL CN–235, CN–235–100, CN–235– 

200, AND CN–235–300 AIRPLANES

Manufacturer’s Serial No. Elevator hinge fitting Compliance time for initial eddy current inspection 

(MSN) (part No.) (whichever occurs later) 

MSN001 through MSN154 

inclusive.

35–31193–0201 

35–31193–0202 

Before exceeding 8,800 flight cycles since first flight of 

the airplane; or before exceeding the applicable flight 

hours since first flight of the airplane as calculated in 

table 2 to paragraph (i)(1) of this AD; whichever occurs 

first.

Within 300 flight cycles 

after the effective date 

of this AD. 

MSN155 through MSN241 

inclusive.

35–31193–0501 

35–31193–0502 

Before exceeding 3,600 flight cycles since first flight of 

the airplane; or before exceeding the applicable flight 

hours since first flight of the airplane as calculated in 

table 2 to paragraph (i)(1) of this AD; whichever occurs 

first.

Within 300 flight cycles 

after the effective date 

of this AD. 

MSN242 through MSN999 

inclusive.

35–31193–0503 

35–31193–0504 

Before exceeding 1,000 flight cycles since first flight of 

the airplane; or before exceeding the applicable flight 

hours since first flight of the airplane as calculated in 

table 2 to paragraph (i)(1) of this AD; whichever occurs 

first.

Within 50 flight cycles 

after the effective date 

of this AD. 

TABLE 2 TO PARAGRAPH (i)(1) OF THIS AD—FLIGHT CYCLES TO FLIGHT HOURS CONVERSION SINCE FIRST FLIGHT OF

THE AIRPLANE

CN–235 Model/version Civilian or military 

type certificate Flight cycles to flight hours conversion 

CN–235 (Commercial Identification S10) Civilian ................... Flight hours since first flight of the airplane = the applicable flight cycles from 

table 1 to paragraph (i)(1) of this AD × 0.861. 

CN–235–100 ........................................... Civilian ................... Flight hours since first flight of the airplane = the applicable flight cycles from 

table 1 to paragraph (i)(1) of this AD × 0.861. 

CN–235–200 ........................................... Civilian ................... Flight hours since first flight of the airplane = the applicable flight cycles from 

table 1 to paragraph (i)(1) of this AD × 0.806. 

CN–235–300 ........................................... Civilian ................... Flight hours since first flight of the airplane = the applicable flight cycles from 

table 1 to paragraph (i)(1) of this AD × 0.861. 

CN–235 (Commercial Identification 

S10M).

Military ................... Flight hours since first flight of the airplane = the applicable flight cycles from 

table 1 to paragraph (i)(1) of this AD × 0.861. 

CN–235–100M ........................................ Military ................... Flight hours since first flight of the airplane = the applicable flight cycles from 

table 1 to paragraph (i)(1) of this AD × 2.222. 

CN–235–200M ........................................ Military ................... Flight hours since first flight of the airplane = the applicable flight cycles from 

table 1 to paragraph (i)(1) of this AD × 2.222. 

CN–235–300M ........................................ Military ................... Flight hours since first flight of the airplane = the applicable flight cycles from 

table 1 to paragraph (i)(1) of this AD × 2.167. 

CN–235–100M/IR01 ............................... Military ................... Flight hours since first flight of the airplane = the applicable flight cycles from 

table 1 to paragraph (i)(1) of this AD × 1.389. 

CN–235–100M/EA02V ............................ Military ................... Flight hours since first flight of the airplane = the applicable flight cycles from 

table 1 to paragraph (i)(1) of this AD × 1.389. 

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Federal Register / Vol. 82, No. 170 / Tuesday, September 5, 2017 / Rules and Regulations 41881 

TABLE 2 TO PARAGRAPH (i)(1) OF THIS AD—FLIGHT CYCLES TO FLIGHT HOURS CONVERSION SINCE FIRST FLIGHT OF

THE AIRPLANE—Continued 

CN–235 Model/version Civilian or military 

type certificate Flight cycles to flight hours conversion 

CN–235–200M/CL02 .............................. Military ................... Flight hours since first flight of the airplane = the applicable flight cycles from 

table 1 to paragraph (i)(1) of this AD × 1.389. 

CN–235/EA01F (Commercial Identification S10M).Military ................... Flight hours since first flight of the airplane = the applicable flight cycles from 

table 1 to paragraph (i)(1) of this AD × 0.861. 

CN–235–300/SM01 ................................. Civilian ................... Flight hours since first flight of the airplane = the applicable flight cycles from 

table 1 to paragraph (i)(1) of this AD × 3.125. 

CN–235 –300M/CG01, –300M/GC01, 

–300/MM01, –300/CL04.

Military ................... Flight hours since first flight of the airplane = the applicable flight cycles from 

table 1 to paragraph (i)(1) of this AD × 3.125. 

(2) Repeat the eddy current inspection 

specified in paragraph (i)(1) of this AD 

thereafter within the applicable interval 

specified in table 3 to paragraph (i)(2) of this 

AD. 

TABLE 3 TO PARAGRAPH (i)(2) OF THIS AD—REPETITIVE INSPECTION INTERVALS

Manufacturer’s serial No. 

Elevator attachment fitting 

(P/N) 

Compliance time for repetitive eddy current inspections 

MSN001 through MSN154 inclusive ....... 35–31193–0201 

35–31193–0202 

Before exceeding 1,300 flight cycles since the most recent inspection; or before 

exceeding the applicable flight hours since the most recent inspection as calculated in table 4 to paragraph (i)(2) of this AD; whichever occurs first. 

MSN155 through MSN241 inclusive ....... 35–31193–0501 

35–31193–0502 

Before exceeding 1,000 flight cycles since the most recent inspection; or before 

exceeding the applicable flight hours since the most recent inspection as calculated in table 4 to paragraph (i)(2) of this AD; whichever occurs first. 

MSN242 through MSN999 inclusive ....... 35–31193–0503 

35–31193–0504 

Before exceeding 1,000 flight cycles since the most recent inspection; or before 

exceeding the applicable flight hours since the most recent inspection as calculated in table 4 to paragraph (i)(2) of this AD; whichever occurs first. 

TABLE 4 TO PARAGRAPH (i)(2) OF THIS AD—FLIGHT CYCLES TO FLIGHT HOURS CONVERSION FOR REPETITIVE

INSPECTIONS

CN–235 Model/version Civilian or military 

type certificate Flight cycles to flight hours conversion 

CN–235 (Commercial Identification S10) Civilian ................... Flight hours since most recent inspection = the applicable flight cycles from 

table 3 to paragraph (i)(2) of this AD × 0.861. 

CN–235–100 ........................................... Civilian ................... Flight hours since most recent inspection = the applicable flight cycles from 

table 3 to paragraph (i)(2) of this AD × 0.861. 

CN–235–200 ........................................... Civilian ................... Flight hours since most recent inspection = the applicable flight cycles from 

table 3 to paragraph (i)(2) of this AD × 0.806. 

CN–235–300 ........................................... Civilian ................... Flight hours since first flight of the airplane = the applicable flight cycles from 

table 3 to paragraph (i)(2) of this AD × 0.861. 

CN–235 (Commercial Identification 

S10M).

Military ................... Flight hours since most recent inspection = the applicable flight cycles from 

table 3 to paragraph (i)(2) of this AD × 0.861. 

CN–235–100M ........................................ Military ................... Flight hours since most recent inspection = the applicable flight cycles from 

table 3 to paragraph (i)(2) of this AD × 2.222. 

CN–235–200M ........................................ Military ................... Flight hours since most recent inspection = the applicable flight cycles from 

table 3 to paragraph (i)(2) of this AD × 2.222. 

CN–235–300M ........................................ Military ................... Flight hours since most recent inspection = the applicable flight cycles from 

table 3 to paragraph (i)(2) of this AD × 2.167. 

CN–235–100M/IR01 ............................... Military ................... Flight hours since most recent inspection = the applicable flight cycles from 

table 3 to paragraph (i)(2) of this AD × 1.389. 

CN–235–100M/EA02V ............................ Military ................... Flight hours since most recent inspection = the applicable flight cycles from 

table 3 to paragraph (i)(2) of this AD × 1.389. 

CN–235–200M/CL02 .............................. Military ................... Flight hours since most recent inspection = the applicable flight cycles from 

table 3 to paragraph (i)(2) of this AD × 1.389. 

CN–235/EA01F (Commercial Identification S10M).Military ................... Flight hours since most recent inspection = the applicable flight cycles from 

table 3 to paragraph (i)(2) of this AD × 0.861. 

CN–235–300/SM01 ................................. Civilian ................... Flight hours since most recent inspection = the applicable flight cycles from 

table 3 to paragraph (i)(2) of this AD × 3.125. 

CN–235 –300M/CG01, –300M/GC01, 

–300/MM01, –300/CL04.

Military ................... Flight hours since most recent inspection = the applicable flight cycles from 

table 3 to paragraph (i)(2) of this AD × 3.125. 

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(j) Repetitive Eddy Current Inspections— 

Model C–295 Airplanes 

For Model C–295 airplanes: Do the actions 

required by paragraphs (j)(1) and (j)(2) of this 

AD. 

(1) At the later of the times specified in 

table 5 to paragraph (j)(1) of this AD: Do an 

eddy current inspection of the elevator hinge 

fitting and attachment fitting to detect cracks, 

in accordance with the instructions of Airbus 

Defense and Space S.A. AOT AOT–C295–55– 

0003, dated December 22, 2015. 

TABLE 5 TO PARAGRAPH (j)(1) OF THIS AD—INITIAL COMPLIANCE TIMES FOR MODEL C–295 AIRPLANES

C–295 Model/Version Manufacturer’s Serial 

Number 

(MSN) 

Elevator Hinge 

Fitting 

(Part Number) 

Compliance time for initial eddy current inspection 

(whichever occurs later) 

C–295M/ EA03(01–10), 

RJ01 (01–02), 

PO01(01–08), 

AG01(01–06), 

BR01(01–03).

MSN001 through 

MSN030 inclusive.

95–31193–0501 

95–31193–0502 

Since first flight of the airplane: Before exceeding 3,600 flight cycles; or before exceeding 5,040 flight hours; whichever occurs first.Within 300 flight cycles 

after the effective 

date of this AD. 

C–295M (from MSN 

031).

MSN031 through 

MSN999 inclusive.

95–31193–0503 

95–31193–0504 

Since first flight of the airplane: Before exceeding 1,000 flight cycles; or before exceeding 1,400 flight hours; whichever occurs first.Within 50 flight cycles 

after the effective 

date of this AD. 

C–295M/FI01, FI02 ....... MSN031 through 

MSN999 inclusive.

95–31193–0503 

95–31193–0504 

Since first flight of the airplane: Before exceeding 1,000 flight cycles; or before exceeding 1,000 flight hours; whichever occurs first.Within 50 flight cycles 

after the effective 

date of this AD. 

C–295M/PG01 .............. MSN031 through 

MSN999 inclusive.

95–31193–0503 

95–31193–0504 

Since first flight of the airplane: Before exceeding 1,000 flight cycles; or before exceeding 1,400 flight hours; whichever occurs first.Within 50 flight cycles 

after the effective 

date of this AD. 

C–295M/PG02, PG03 ... MSN031 through 

MSN999 inclusive.

95–31193–0503 

95–31193–0504 

Since first flight of the airplane: Before exceeding 1,000 flight cycles; or before exceeding 1,900 flight hours; whichever occurs first.Within 50 flight cycles 

after the effective 

date of this AD. 

C–295M/CH01 .............. MSN031 through 

MSN999 inclusive.

95–31193–0503 

95–31193–0504 

Since first flight of the airplane: Before exceeding 1,000 flight cycles; or before exceeding 1,200 flight hours; whichever occurs first.Within 50 flight cycles 

after the effective 

date of this AD. 

C–295M/CH02, OM03 .. MSN031 through 

MSN999 inclusive.

95–31193–0503 

95–31193–0504 

Since first flight of the airplane: Before exceeding 1,000 flight cycles; or before exceeding 1,500 flight hours; whichever occurs first.Within 50 flight cycles 

after the effective 

date of this AD. 

C–295MW ..................... MSN031 through 

MSN999 inclusive.

95–31193–0503 

95–31193–0504 

Since first flight of the airplane: Before exceeding 1,000 flight cycles; or before exceeding 1,400 flight hours; whichever occurs first.Within 50 flight cycles 

after the effective 

date of this AD. 

(2) Repeat the eddy current inspection 

specified in paragraph (j)(1) of this AD 

thereafter within the applicable interval 

specified in table 6 to paragraph (j)(2) of this 

AD. 

TABLE 6 TO PARAGRAPH (j)(2) OF THIS AD—REPETITIVE INSPECTION INTERVALS FOR MODEL C–295 AIRPLANES

C–295 Model/version Manufacturer’s serial No. 

(MSN) 

Elevator hinge 

fitting 

(part number) 

Compliance time for repetitive eddy current inspections 

C–295M/ EA03(01–10), RJ01 

(01–02), PO01(01–08), 

AG01(01–06), BR01(01– 

03).

MSN001 through MSN030 inclusive.95–31193–0501 

95–31193–0502 

Before exceeding 1,000 flight cycles since the most recent 

inspection; or before exceeding 1,400 flight hours since 

the most recent inspection; whichever occurs first. 

C–295M (from MSN 031) ...... MSN031 through MSN999 inclusive.95–31193–0503 

95–31193–0504 

Before exceeding 1,000 flight cycles since the most recent 

inspection; or before exceeding 1,400 flight hours since 

the most recent inspection; whichever occurs first. 

C–295M/FI01, FI02 ............... MSN031 through MSN999 inclusive.95–31193–0503 

95–31193–0504 

Before exceeding 1,000 flight cycles since the most recent 

inspection; or before exceeding 1,000 flight hours since 

the most recent inspection; whichever occurs first. 

C–295M/PG01 ....................... MSN031 through MSN999 inclusive.95–31193–0503 

95–31193–0504 

Before exceeding 1,000 flight cycles since the most recent 

inspection; or before exceeding 1,400 flight hours since 

the most recent inspection; whichever occurs first. 

C–295M/PG02, PG03 ........... MSN031 through MSN999 inclusive.95–31193–0503 

95–31193–0504 

Before exceeding 1,000 flight cycles since the most recent 

inspection; or before exceeding 1,900 flight hours since 

the most recent inspection; whichever occurs first. 

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Federal Register / Vol. 82, No. 170 / Tuesday, September 5, 2017 / Rules and Regulations 41883 

TABLE 6 TO PARAGRAPH (j)(2) OF THIS AD—REPETITIVE INSPECTION INTERVALS FOR MODEL C–295 AIRPLANES— 

Continued 

C–295 Model/version Manufacturer’s serial No. 

(MSN) 

Elevator hinge 

fitting 

(part number) 

Compliance time for repetitive eddy current inspections 

C–295M/CH01 ....................... MSN031 through MSN999 inclusive.95–31193–0503 

95–31193–0504 

Before exceeding 1,000 flight cycles since the most recent 

inspection; or before exceeding 1,200 flight hours since 

the most recent inspection; whichever occurs first. 

C–295M/CH02, OM03 ........... MSN031 through MSN999 inclusive.95–31193–0503 

95–31193–0504 

Before exceeding 1,000 flight cycles since the most recent 

inspection; or before exceeding 1,500 flight hours since 

the most recent inspection; whichever occurs first. 

C–295MW .............................. MSN031 through MSN999 inclusive.95–31193–0503 

95–31193–0504 

Before exceeding 1,000 flight cycles since the most recent 

inspection; or before exceeding 1,400 flight hours since 

the most recent inspection; whichever occurs first. 

(k) Corrective Action for Discrepancies 

Found During Eddy Current Inspection 

If, during any inspection required by 

paragraph (i)(1), (i)(2), (j)(1), or (j)(2) of this 

AD, any crack is detected, as defined in 

Airbus Defense and Space S.A. AOT AOT– 

CN235–55–0003, dated December 22, 2015; 

or AOT AOT–C295–55–0003, dated 

December 22, 2015; as applicable: Before 

further flight, accomplish applicable 

corrective actions in accordance with the 

instructions of Airbus Defense and Space 

S.A. AOT AOT–CN235–55–0003, dated 

December 22, 2015; or AOT AOT–C295–55– 

0003, dated December 22, 2015; as 

applicable. Where Airbus Defense and Space 

S.A. AOT AOT–CN235–55–0003, dated 

December 22, 2015; or AOT AOT–C295–55– 

0003, dated December 22, 2015; specifies to 

contact Airbus Defense and Space S.A. for 

corrective actions, before further flight, 

accomplish corrective actions in accordance 

with the procedures specified in paragraph 

(n)(2) of this AD. 

(l) Provision Regarding Terminating Action 

Accomplishing corrective actions, as 

required by paragraph (k) of this AD, does 

not constitute terminating action for the 

repetitive inspections required by paragraphs 

(i)(2) and (j)(2) of this AD, unless explicitly 

stated in the approved method of compliance 

for the corrective action. 

(m) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus 

Defense and Space S.A. AOT AOT–CN235– 

55–0001, Revision 1, dated March 6, 2015; or 

AOT AOT–C295–55–0001, Revision 1, dated 

May 29, 2014. 

(n) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards Branch, 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. 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. 

(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 Section, 

Transport Standards Branch, FAA; or the 

European Aviation Safety Agency (EASA); or 

Airbus Defense and Space S.A.’s EASA DOA. 

If approved by the DOA, the approval must 

include the DOA-authorized signature. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2016–0075, dated April 19, 2016, 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–2016–9521. 

(2) For more information about this AD, 

contact Shahram Daneshmandi, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 1601 Lind Avenue 

SW., Renton, WA 98057–3356; telephone: 

425–227–1112; fax: 425–227–1149. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (p)(3) and (p)(4) of this AD. 

(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 Defense and Space S.A. Alert 

Operators Transmission (AOT) AOT–CN235– 

55–0001, Revision 2, dated March 10, 2015. 

(ii) Airbus Defense and Space S.A. AOT 

AOT–CN235–55–0003, dated December 22, 

2015. 

(iii) Airbus Defense and Space S.A. AOT 

AOT–C295–55–0001, Revision 2, dated April 

9, 2015. 

(iv) Airbus Defense and Space S.A. AOT 

AOT–C295–55–0003, dated December 22, 

2015. 

(3) For service information identified in 

this AD, contact Airbus Defense and Space, 

Services/Engineering Support, Avenida de 

Arago ́n 404, 28022 Madrid, Spain; fax +34 91 

585 31 27; email MTA.TechnicalService@

airbus.com. 

(4) You may view this service information 

at the FAA, Transport Standards Branch, 

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 August 

22, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–18396 Filed 9–1–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF STATE 

22 CFR Part 41 

[Public Notice 9580] 

RIN 1400–AD30 

Visas: Documentation of 

Nonimmigrants Under the Immigration 

and Nationality Act, as Amended 

AGENCY: Department of State. 

ACTION: Final rule. 

SUMMARY: This final rule clarifies 

procedures for waiver of documentary 

requirements due to an unforeseen 

emergency for nonimmigrants seeking 

admission to the United States. 

DATES: This rule is effective on October 

5, 2017. 

FOR FURTHER INFORMATION CONTACT: 

Megan B. Herndon, Legislation and 

Regulations Division, Legal Affairs, 

Office of Visa Services, Bureau of 

Consular Affairs, Department of State, 

600 19th St. NW., Washington, DC 

20006 (202) 485–7440. 

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