Federal Register / Vol. 81, No. 170 / Thursday, September 1, 2016 / Rules and Regulations 60243 

model series of airplanes. It is not a rule 

of general applicability. 

The substance of these special 

conditions has been subjected to the 

notice and comment period in several 

prior instances and has been derived 

without substantive change from those 

previously issued. It is unlikely that 

prior public comment would result in a 

significant change from the substance 

contained herein. Therefore, the FAA 

has determined that prior public notice 

and comment are unnecessary, and good 

cause exists for adopting these special 

conditions upon publication in the 

Federal Register. The FAA is requesting 

comments to allow interested persons to 

submit views that may not have been 

submitted in response to the prior 

opportunities for comment described 

above. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

■ The authority citation for these 

special conditions is as follows: 

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

44702, 44704. 

The Special Conditions 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the following special conditions are 

issued as part of the type certification 

basis for Bombardier Model BD–700– 

2A12 and BD–700–2A13 airplanes. 

1. In addition to meeting the 

requirements of § 25.773(b)(1), the 

airplane must have a means to maintain 

a clear portion of the windshield, during 

precipitation conditions, such that both 

pilots to have a sufficiently extensive 

view along the ground or flight path in 

taxi and flight. This means must be 

designed to function, without 

continuous attention on the part of the 

crew, in conditions from light misting 

precipitation to heavy rain, at speeds 

from fully stopped in still air to 1.5 VSR1

with lift and drag devices retracted, and 

in icing conditions specified in 

§ 25.1419 if certification for flight in 

icing conditions is requested. 

2. The precipitation removal system 

must comply with § 25.773. 

3. Instructions to maintain the 

precipitation-removal system must 

comply with § 25.1529. 

4. The materials used in the 

precipitation removal system must 

comply with § 25.603. 

Issued in Renton, Washington, on August 

23, 2016. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–21079 Filed 8–31–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–7048; Directorate 

Identifier 2016–CE–014–AD; Amendment 

39–18635; AD 2016–18–05] 

RIN 2120–AA64 

Airworthiness Directives; PILATUS 

AIRCRAFT LTD. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

PILATUS AIRCRAFT LTD. Models PC– 

12, PC–12/45, PC–12/47, and PC–12/ 

47E airplanes installed with an affected 

engine mounting frame assembly. This 

AD results from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as longitudinal material 

separation on the internal surface of the 

engine mounting frame assembly tubes. 

We are issuing this AD to detect and 

correct this condition, which could lead 

to partial or complete failure of the 

structural joint and possibly result in inflight detachment of the engine with 

consequent loss of control. 

DATES: This AD is effective October 6, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 6, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

7048; or in person at Document 

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 service information identified in 

this AD, contact Pilatus Aircraft Ltd., 

Customer Support PC–12, CH–6371 

Stans, Switzerland; phone: +41 41 619 

33 33; fax: +41 41 619 73 11; email: 

SupportPC12@pilatus-aircraft.com; 

Internet: www.pilatus-aircraft.com. For 

information on the availability of this 

material at the FAA, call (816) 329– 

4148. It is also available on the Internet 

at http://www.regulations.gov by 

searching for Docket No. FAA–2016– 

7048. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090; email: 

doug.rudolph@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 PILATUS AIRCRAFT LTD. 

Models PC–12, PC–12/45, PC–12/47, 

and PC–12/47E airplanes installed with 

an affected engine mounting frame 

assembly. The NPRM was published in 

the Federal Register on June 13, 2016 

(81 FR 38115). The NPRM proposed to 

correct an unsafe condition for the 

specified products and was based on 

mandatory continuing airworthiness 

information (MCAI) originated by an 

aviation authority of another country. 

The MCAI states: 

The PC–12 Engine Mounting Frame 

Assembly (hereafter referred to as ‘‘EMF’’ in 

this AD), Part Number (P/N) 571.20.12.036, is 

a welded structure including three special 

tubes, P/N 571.20.12.073, P/N 571.20.12.074 

and P/N 571.20.12.107, the ends of which are 

subject to a special swaging process during 

manufacturing. Longitudinal material 

separation on the internal surface of the 

special tubes was detected on few EMFs on 

new production aeroplanes. Investigations 

identified the root cause to be an incorrect 

accomplishment of the swaging process. 

This condition, if not detected and 

corrected, could lead to growth of the 

material separation and subsequent partial or 

complete failure of the structural joint, 

possibly resulting in in-flight detachment of 

the engine and consequent reduced control, 

or loss of control, of the aeroplane. 

To address this potential unsafe condition, 

Pilatus issued Service Bulletin (SB) No. 71– 

009, now at Revision 2 (hereafter referred to 

as ‘‘the SB’’ in this AD), to provide 

inspection instructions for the affected EMF 

to detect indications of material separation. 

For the reason described above, this AD 

requires identification and inspection of the 

affected EMF and, depending on the findings, 

their replacement with serviceable EMF. 

The MCAI can be found in the AD 

docket on the Internet at: https:// 

www.regulations.gov/ 

document?D=FAA-2016-7048-0002. 


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60244 Federal Register / Vol. 81, No. 170 / Thursday, September 1, 2016 / Rules and Regulations 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (81 

FR 38115, June 13, 2016) 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 the 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 (81 FR 

38115, June 13, 2016) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (81 FR 38115, 

June 13, 2016). 

Related Service Information Under 1 

CFR Part 51 

We reviewed PILATUS AIRCRAFT 

LTD. PILATUS PC–12 Service Bulletin 

No: 71–009, Reference No: 345, 

Modification No: EC–15–0632, Revision 

2, dated March 18, 2016; Pilatus 

Powerplant Mounting Frame, Removal/ 

Installation, Date module/Technical 

publication 12–A–71–00–05–00A– 

920A–A, dated February 26, 2010, 

found in Pilatus Model type–PC–12, 

PC–12/45, PC–12/47 MSN–101–888 

Aircraft Maintenance Manual (AMM), 

Document No. 02049, 12–A–AM–00– 

00–00–I; and Pilatus Powerplant 

Mounting Frame, Removal/Installation, 

Date module/Technical publication 12– 

B–71–00–05–00A–920A–A, dated 

October 4, 2010, found in Pilatus Model 

type–PC–12/47E MSN–1001–UP 

Aircraft Maintenance Manual (AMM), 

Document No. 02300, 12–B–AM–00– 

00–00–I. The service information 

describes procedures for determining if 

an affected engine mounting frame 

assembly (EMF) is installed, inspecting 

the EMF, and replacing the EMF with a 

serviceable EMF. 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 of this AD. 

Costs of Compliance 

We estimate that this AD will affect 

888 products of U.S. registry. We also 

estimate that it would take about 3 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate 

the cost of this AD on U.S. operators to 

be $226,440, or $255 per product. 

In addition, we estimate that any 

necessary follow-on actions would cost 

the following amounts. We have no way 

of determining the number of products 

that may need these actions. 

The visual and eddy current 

inspections would take about 3 workhours for a cost of $255 per product. 

The replacement of the EMF would 

take about 90 work-hours and require 

parts costing $33,336, for a cost of 

$40,986 per product. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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 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. 

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– 

7048; 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 the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone (800) 647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

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 AD: 

2016–18–05 PILATUS AIRCRAFT LTD.: 

Amendment 39–18635; Docket No. 

FAA–2016–7048; Directorate Identifier 

2016–CE–014–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective October 6, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to PILATUS AIRCRAFT 

LTD. Models PC–12, PC–12/45, PC–12/47, 

and PC–12/47E airplanes, all serial numbers, 

that are: 

(1) Installed with an affected serial number 

engine mounting frame assembly (EMF), part 

number (P/N) 571.20.12.036, listed in figure 

1 of paragraph (c)(1) of this AD; and 

FIGURE 1 TO PARAGRAPH (c)(1) OF

THIS AD: EMF P/N 571.20.12.036, 

AFFECTED SERIAL NUMBERS

0001 through 1200 inclusive. 

1202 through 1272 inclusive. 

1275 through 1323 inclusive. 

1325 through 1328 inclusive. 


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Federal Register / Vol. 81, No. 170 / Thursday, September 1, 2016 / Rules and Regulations 60245 

FIGURE 1 TO PARAGRAPH (c)(1) OF

THIS AD: EMF P/N 571.20.12.036, 

AFFECTED SERIAL NUMBERS—Continued 

1334 through 1338 inclusive. 

1340 and 1342. 

1344 through 1346 inclusive. 

1348 and 1349. 

1358, 1361, and 1365. 

(2) Certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 71: Power Plant. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as 

longitudinal material separation on the 

internal surface of the engine mounting frame 

assembly tubes (EMF). We are issuing this 

AD to detect and correct material separation 

on the internal surface of the engine 

mounting frame assembly tubes, which could 

lead to partial or complete failure of the 

structural joint and possibly result in inflight detachment of the engine with 

consequent loss of control. 

(f) Actions and Compliance 

Do the actions in paragraphs (f)(1) through 

(7) of this AD. If paragraphs (f)(1) through (6) 

of this AD have already been done before 

October 6, 2016 (the effective date of this 

AD), then only paragraph (f)(7) of this AD 

applies. 

(1) Within the compliance time identified 

in figure 2 of paragraph (f)(1) of this AD, do 

an ultrasonic inspection of the swaged engine 

mounting tube ends of the affected EMF 

following the instructions of paragraph 

3.B.(1) of PILATUS AIRCRAFT LTD 

PILATUS PC–12 Service Bulletin No: 71– 

009, Reference No: 345, Modification No: 

EC–15–0632, Revision 2, dated March 18, 

2016. 

FIGURE 2 TO PARAGRAPH (f)(1) OF

THIS AD: INITIAL COMPLIANCE TIME

A or B, Whichever Occurs Later 

A ........... Before the EMF exceeds 11,000 

hours time-in-service (TIS) or 

13,500 flight cycles (FC), whichever occurs first since first installation of the EMF on an airplane. 

B ........... Within 1,000 hours TIS or 1,000 

FC or 6 months, whichever occurs first after October 6, 2016 

(the effective date of this AD). 

(2) If an indication with an echo of less 

than 40 percent full screen height is detected 

on an EMF during the ultrasonic inspection 

required in paragraph (f)(1) of this AD, except 

for paragraph (f)(7), no further actions are 

required for this AD. Document compliance 

with this AD in the maintenance records. 

(3) If an indication with an echo of 40 

percent full screen height or more is detected 

on an EMF during the ultrasonic inspection 

required in paragraph (f)(1) of this AD, do the 

actions in paragraphs (f)(3)(i) through (iii) of 

this AD, as applicable. 

(i) Before further flight and repetitively 

thereafter at intervals not to exceed 600 hours 

TIS or 12 months, whichever occurs first, do 

a visual inspection of the welding and do an 

eddy current inspection of the tubes at the 

indication point detected during the 

ultrasonic inspection. Use the instructions of 

paragraphs 3.B.(2) and 3.B.(3) of PILATUS 

AIRCRAFT LTD PILATUS PC–12 Service 

Bulletin No: 71–009, Reference No: 345, 

Modification No: EC–15–0632, Revision 2, 

dated March 18, 2016. 

(ii) If any cracks are found during any of 

the visual inspections or if an indication with 

a signal of 20 percent or more is detected 

during any of the eddy current inspections 

required in paragraph (f)(3)(i) of this AD, 

before further flight, replace the EMF with a 

serviceable EMF following the instructions in 

the service information listed in paragraph 

(f)(5) of this AD, including all subparagraphs 

as applicable. 

(iii) Unless already done as required by 

paragraph (f)(3)(ii) of this AD, with≤in 1,800 

hours TIS or 36 months after the initial visual 

and eddy current inspections of the affected 

EMF required by paragraph (f)(3)(i) of this 

AD, whichever occurs first, replace the EMF 

with a serviceable EMF following the 

instructions in the service information listed 

in paragraph (f)(5) of this AD, including all 

subparagraphs as applicable. 

(4) For the purpose of this AD, a 

serviceable EMF is defined as any EMF that 

is not listed in figure 1 of paragraph (c)(1) of 

this AD or an affected EMF that is listed in 

figure 1 of paragraph (c)(1) of this AD but has 

had the ultrasonic inspection required in 

paragraph (f)(1) of this AD and had an 

indication with an echo of less than 40 

percent full screen height. 

(5) For replacement of the EMF, follow the 

instructions listed in paragraphs (f)(5)(i) and 

(ii), as applicable. 

(i) For Models PC–12, PC–12/45, and PC– 

12/47, manufacturer serial numbers (MSN) 

101–888: Pilatus Powerplant Mounting 

Frame, Removal/Installation, Date module/ 

Technical publication 12–A–71–00–05–00A– 

920A–A, dated February 26, 2010, found in 

Pilatus Model type-PC–12, PC–12/45, PC–12/ 

47 MSN–101–888 Aircraft Maintenance 

Manual (AMM), Document No. 02049, 12–A– 

AM–00–00–00–I. 

(ii) For Model PC–12/47E, MSN 1001 and 

up: Pilatus Powerplant Mounting Frame, 

Removal/Installation, Date module/Technical 

publication 12–B–71–00–05–00A–920A–A, 

dated October 4, 2010, found in Pilatus 

Model type-PC–12/47E MSN–1001–UP 

Aircraft Maintenance Manual (AMM), 

Document No. 02300, 12–B–AM–00–00–00– 

I. 

(6) If an EMF has an indication with an 

echo of 40 percent or more during the 

ultrasonic inspection required in paragraph 

(f)(1) of this AD, you may replace the EMF 

with a serviceable EMF in lieu of the visual 

or eddy current inspections required in 

paragraph (f)(3)(i) of this AD. For 

replacement of the EMF, follow the 

instructions in the service information listed 

in paragraph (f)(5) of this AD, including all 

subparagraphs as applicable. 

(7) As of October 6, 2016 (the effective date 

of this AD), do not install an EMF P/N 

571.20.12.036 unless it has been determined 

to be a serviceable EMF as specified in 

paragraph (f)(4) of this AD. 

(8) Airplanes with an MSN of 1556 or 

higher are not affected by this AD provided 

that the EMF has not been replaced since its 

manufacture. A review of the maintenance 

records, Airworthiness Approval Tag (FAA 

Form 8130–3), or other positive form of parts 

identification such as a shipping ticket, 

invoice, or direct ship authority letter, can be 

used to determine the serial number of the 

EMF. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4059; fax: (816) 329– 

4090; email: doug.rudolph@faa.gov. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(h) Related Information 

(1) Refer to MCAI European Aviation 

Safety Agency (EASA) AD No. 2016–0081, 

dated April 25, 2016, for related information 

pertaining to this AD. The MCAI can be 

found in the AD docket on the Internet at: 

https://www.regulations.gov/ 

document?D=FAA-2016-7048-0002. 

(i) 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) PILATUS PC–12 Service Bulletin No: 

71–009, Reference No: 345, Modification No: 

EC–15–0632, Revision 2, dated March 18, 

2016; 

(ii) Pilatus Powerplant Mounting Frame, 

Removal/Installation, Date module/Technical 

publication 12–A–71–00–05–00A–920A–A, 

dated February 26, 2010, found in Pilatus 

Model type-PC–12, PC–12/45, PC–12/47 

MSN–101–888 Aircraft Maintenance Manual 


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60246 Federal Register / Vol. 81, No. 170 / Thursday, September 1, 2016 / Rules and Regulations 

(AMM), Document No. 02049, 12–A–AM– 

00–00–00–I; and 

(iii) Pilatus Powerplant Mounting Frame, 

Removal/Installation, Date module/Technical 

publication 12–B–71–00–05–00A–920A–A, 

dated October 4, 2010, found in Pilatus 

Model type- PC–12/47E MSN–1001–UP 

Aircraft Maintenance Manual (AMM), 

Document No. 02300, 12–B–AM–00–00–00– 

I. 

(3) For service information identified in 

this AD, contact Pilatus Aircraft Ltd., 

Customer Support PC–12, CH–6371 Stans, 

Switzerland; phone: +41 41 619 33 33; fax: 

+41 41 619 73 11; email: 

SupportPC12@pilatus-aircraft.com; Internet: 

www.pilatus-aircraft.com. 

(4) You may view this 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. In 

addition, you can access this service 

information on the Internet at http:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2016–7048. 

(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 August 

23, 2016. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–20833 Filed 8–31–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–5460; Directorate 

Identifier 2015–NM–188–AD; Amendment 

39–18599; AD 2016–16–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting an 

airworthiness directive (AD) that 

published in the Federal Register. That 

AD applies to certain Airbus Model 

A330–200 Freighter, –200, and –300 

series airplanes. Paragraphs (i) and (l) of 

the regulatory text contain 

typographical errors in the service 

bulletin number. This document 

corrects those errors. In all other 

respects, the original document remains 

the same. 

DATES: This final rule is effective 

September 8, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 8, 2016 (81 FR 51325, 

August 4, 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 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2016–5460. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; 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: 

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: 

Airworthiness Directive 2016–16–01, 

Amendment 39–18599 (81 FR 51325, 

August 4, 2016) (‘‘AD 2016–16–01’’), 

currently requires an inspection of 

affected structural parts in the cargo and 

cabin compartments to determine if 

proper heat treatment has been done, 

and replacement if necessary, for certain 

Airbus Model A330–200 Freighter, 

–200, and –300 series airplanes. 

Need for the Correction 

As published, paragraphs (i) and (l) of 

the regulatory text identify the service 

information by the wrong service 

bulletin number. Where paragraphs (i) 

and (l) incorrectly specify Airbus 

Service Bulletins ‘‘A320–53–3227’’ and 

‘‘A320–53–3228,’’ the correct service 

bulletin numbers are ‘‘A330–53–3227’’ 

and ‘‘A330–53–3228,’’ respectively. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information: 

• Airbus Service Bulletin A330–53– 

3227, dated August 18, 2015. The 

service information describes 

procedures to inspect affected structural 

parts in the cargo compartment to 

determine if proper heat treatment has 

been done, and replacement of parts; 

and 

• Airbus Service Bulletin A330–53– 

3228, dated August 18, 2015. The 

service information describes 

procedures to inspect affected structural 

parts in the cabin compartment to 

determine if proper heat treatment has 

been done, and replacement of parts. 

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. 

Correction of Publication 

This document corrects two errors 

and correctly adds the AD as an 

amendment to 14 CFR 39.13. Although 

no other part of the preamble or 

regulatory information has been 

corrected, we are publishing the entire 

rule in the Federal Register. 

The effective date of this AD remains 

September 8, 2016. 

Since this action only corrects a 

typographical error in two locations, it 

has no adverse economic impact and 

imposes no additional burden on any 

person. Therefore, we have determined 

that notice and public procedures are 

unnecessary. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Correction 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration amends part 39 of the 

Federal Aviation Regulations (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. 


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