Federal Register / Vol. 81, No. 170 / Thursday, September 1, 2016 / Rules and Regulations 60241 

of the regulations listed in type 

certificate no. T00003NY, or the 

applicable regulations in effect on the 

date of application for the change, 

except for earlier amendments as agreed 

upon by the FAA. 

If the Administrator finds that the 

applicable airworthiness regulations 

(i.e., 14 CFR part 25) do not contain 

adequate or appropriate safety standards 

for the BD–700–2A12 and BD–700– 

2A13 airplanes because of a novel or 

unusual design feature, special 

conditions are prescribed under the 

provisions of § 21.16. 

Special conditions are initially 

applicable to the model for which they 

are issued. Should the type certificate 

for that model be amended later to 

include any other model that 

incorporates the same novel or unusual 

design feature, or should any other 

model already included on the same 

type certificate be modified to 

incorporate the same novel or unusual 

design feature, these special conditions 

would also apply to the other model 

under § 21.101. 

In addition to the applicable 

airworthiness regulations and special 

conditions, the Model BD–700–2A12 

and BD–700–2A13 airplanes must 

comply with the fuel-vent and exhaustemission requirements of 14 CFR part 

34, and the noise certification 

requirements of 14 CFR part 36. 

The FAA issues special conditions, as 

defined in 14 CFR 11.19, in accordance 

with § 11.38, and they become part of 

the type-certification basis under 

§ 21.101. 

Novel or Unusual Design Features 

The Bombardier Inc. Model BD–700– 

2A12 and BD–700–2A13 airplanes will 

have a novel or unusual design feature 

associated with sidestick controllers 

designed to be operated with only one 

hand. 

Discussion 

The Bombardier Aerospace Model 

BD–700–2A12 and BD–700–2A13 

airplanes are equipped with sidestick 

controllers instead of the conventional 

wheel or control stick. This controller is 

designed to be operated using only one 

hand. The requirements of § 25.397(c), 

which define limit pilot forces and 

torques for conventional wheel or stick 

controls, are not adequate for sidestick 

controllers because pilot forces are 

applied to sidestick controllers with 

only the wrist, not arms. Special 

conditions are necessary to specify the 

appropriate loading conditions for 

sidestick controllers. 

These special conditions contain the 

additional safety standards that the 

Administrator considers necessary to 

establish a level of safety equivalent to 

that established by the existing 

airworthiness standards. 

Applicability 

As discussed above, these special 

conditions are applicable to the Model 

BD–700–2A12 and BD–700–2A13 

airplanes. Should Bombardier apply at a 

later date for a change to the type 

certificate to include another model 

incorporating the same novel or unusual 

design feature, these special conditions 

would apply to the other model as well. 

Conclusion 

This action affects only certain novel 

or unusual design features on two 

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. 

In lieu of the pilot forces specified in 

§ 25.397(c), for airplanes equipped with 

sidestick controls designed for force 

application by one wrist and not arms, 

the limit pilot forces are as follows: 

1. For all components between and 

including the handle and its control 

stops. 

Pitch Roll 

Nose up: 200 pounds force 

(lbf).

Nose left: 100 

lbf. 

Pitch Roll 

Nose down: 200 lbf ............... Nose right: 

100 lbf. 

2. For all other components of the 

sidestick control assembly, excluding 

the internal components of the electrical 

sensor assemblies, to avoid damage as a 

result of an in-flight jam. 

Pitch Roll 

Nose up: 125 lbf ................... Nose left: 50 

lbf. 

Nose down: 125 lbf ............... Nose right: 50 

lbf. 

Issued in Renton, Washington, on August 

23, 2016. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–21123 Filed 8–31–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. FAA–2015–6363; Special 

Conditions No. 25–637–SC] 

Special Conditions: Bombardier Inc. 

Model BD–700–2A12 and BD–700– 

2A13 Airplanes; Hydrophobic Coatings 

in Lieu of Windshield Wipers 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special conditions; request 

for comments. 

SUMMARY: These special conditions are 

issued for the Bombardier Inc. 

(Bombardier) Model BD–700–2A12 and 

BD–700–2A13 airplanes. These 

airplanes will have a novel or unusual 

feature when compared to the state of 

technology envisioned in the 

airworthiness standards for transport 

category airplanes. This design feature 

is hydrophobic coatings in lieu of 

windshield wipers. The applicable 

airworthiness regulations do not contain 

adequate or appropriate safety standards 

for these design features. These special 

conditions contain the additional safety 

standards that the Administrator 

considers necessary to establish a level 

of safety equivalent to that established 

by the existing airworthiness standards. 

DATES: This action is effective on 

Bombardier on September 1, 2016. We 

must receive your comments by October 

17, 2016. 


asabaliauskas on DSK3SPTVN1PROD with RULES
60242 Federal Register / Vol. 81, No. 170 / Thursday, September 1, 2016 / Rules and Regulations 

ADDRESSES: Send comments identified 

by docket number FAA–2015–6363 

using any of the following methods: 

• Federal eRegulations Portal: Go to 

http://www.regulations.gov/ and follow 

the online instructions for sending your 

comments electronically. 

• Mail: Send comments to Docket 

Operations, M–30, U.S. Department of 

Transportation (DOT), 1200 New Jersey 

Avenue SE., Room W12–140, West 

Building Ground Floor, Washington, DC 

20590–0001. 

• Hand Delivery or Courier: Take 

comments to Docket Operations in 

Room W12–140 of the West Building 

Ground Floor at 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

• Fax: Fax comments to Docket 

Operations at 202–493–2251. 

Privacy: The FAA will post all 

comments it receives, without change, 

to http://www.regulations.gov/, 

including any personal information the 

commenter provides. Using the search 

function of the docket Web site, anyone 

can find and read the electronic form of 

all comments received into any FAA 

docket, including the name of the 

individual sending the comment (or 

signing the comment for an association, 

business, labor union, etc.). DOT’s 

complete Privacy Act Statement can be 

found in the Federal Register published 

on April 11, 2000 (65 FR 19477–19478), 

as well as at http://DocketsInfo 

.dot.gov/. 

Docket: Background documents or 

comments received may be read at 

http://www.regulations.gov/ at any time. 

Follow the online instructions for 

accessing the docket or go to Docket 

Operations in Room W12–140 of the 

West Building Ground Floor at 1200 

New Jersey Avenue SE., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

FOR FURTHER INFORMATION CONTACT: Bob 

Hettman, FAA, Propulsion and 

Mechanical Systems Branch, ANM–112, 

Transport Airplane Directorate, Aircraft 

Certification Service, 1601 Lind Avenue 

SW., Renton, Washington, 98057–3356; 

telephone 425–227–2683; facsimile 

425–227–1232. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite interested people to take 

part in this rulemaking by sending 

written comments, data, or views. The 

most helpful comments reference a 

specific portion of the special 

conditions, explain the reason for any 

recommended change, and include 

supporting data. 

We will consider all comments we 

receive on or before the closing date for 

comments. We may change these special 

conditions based on the comments we 

receive. 

Background 

On May 30, 2012, Bombardier applied 

for an amendment to type certificate no. 

T00003NY to include the new Model 

BD–700–2A12 and BD–700–2A13 

airplanes. These airplanes are 

derivatives of the Model BD–700 series 

of airplanes currently approved under 

type certificate no. T00003NY, and are 

marketed as the Bombardier Global 7000 

(Model BD–700–2A12) and Global 8000 

(Model BD–700–2A13). These airplanes 

are ultra-long-range, executive-interior 

business jets. 

Type Certification Basis 

Under the provisions of Title 14, Code 

of Federal Regulations (14 CFR) 21.101, 

Bombardier must show that the Model 

BD–700–2A12 and BD–700–2A13 

airplanes meet the applicable provisions 

of the regulations listed in type 

certificate no. T00003NY, or the 

applicable regulations in effect on the 

date of application for the change, 

except for earlier amendments as agreed 

upon by the FAA. 

If the Administrator finds that the 

applicable airworthiness regulations 

(i.e., 14 CFR part 25) do not contain 

adequate or appropriate safety standards 

for the BD–700–2A12 and BD–700– 

2A13 airplanes because of a novel or 

unusual design feature, special 

conditions are prescribed under the 

provisions of § 21.16. 

Special conditions are initially 

applicable to the model for which they 

are issued. Should the type certificate 

for that model be amended later to 

include any other model that 

incorporates the same novel or unusual 

design feature, or should any other 

model already included on the same 

type certificate be modified to 

incorporate the same novel or unusual 

design feature, these special conditions 

would also apply to the other model 

under § 21.101. 

In addition to the applicable 

airworthiness regulations and special 

conditions, the Model BD–700–2A12 

and BD–700–2A13 airplanes must 

comply with the fuel-vent and exhaustemission requirements of 14 CFR part 

34, and the noise certification 

requirements of 14 CFR part 36. 

The FAA issues special conditions, as 

defined in 14 CFR 11.19, in accordance 

with § 11.38, and they become part of 

the type-certification basis under 

§ 21.101. 

Novel or Unusual Design Features 

The Bombardier Model BD–700–2A12 

and BD–700–2A13 airplanes will have a 

novel or unusual design feature 

associated with flightdeck design, 

which incorporates a hydrophobic 

windshield coating to provide adequate 

pilot compartment view in the presence 

of precipitation. Sole reliance on such a 

coating, without windshield wipers, 

constitutes a novel or unusual design 

feature for which the applicable 

airworthiness regulations do not contain 

adequate or appropriate safety 

standards. 

Discussion 

14 CFR 25.773(b)(1) requires a means 

to maintain a sufficiently clear portion 

of the windshield for both pilots to have 

an extensive view along the flight path 

during precipitation conditions. The 

regulations require this means to 

maintain such an area during 

precipitation in heavy rain at speeds up 

to 1.5 VSR1. Hydrophobic windshield 

coatings may depend to some degree on 

airflow to maintain a clear vision area. 

The heavy rain and high speed 

conditions specified in the current rule 

do not necessarily represent the limiting 

condition for this new technology. For 

example, airflow over the windshield, 

which may be necessary to remove 

moisture from the windshield, may not 

be adequate to maintain a sufficiently 

clear area of the windshield in lowspeed flight or during surface 

operations. Alternatively, airflow over 

the windshield may be disturbed during 

such critical times as the approach to 

land, where the airplane is at a higherthan-normal pitch attitude. In these 

cases, areas of airflow disturbance or 

separation on the windshield could 

cause a failure to maintain a clear vision 

area on the windshield. 

These special conditions contain the 

additional safety standards that the 

Administrator considers necessary to 

establish a level of safety equivalent to 

that established by the existing 

airworthiness standards. 

Applicability 

As discussed above, these special 

conditions are applicable to the Model 

BD–700–2A12 and BD–700–2A13 

airplanes. Should Bombardier apply at a 

later date for a change to the type 

certificate to include another model 

incorporating the same novel or unusual 

design feature, these special conditions 

would apply to the other model as well. 

Conclusion 

This action affects only certain novel 

or unusual design features on two 


asabaliauskas on DSK3SPTVN1PROD with RULES
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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