Federal Register / Vol. 80, No. 116 / Wednesday, June 17, 2015 / Rules and Regulations 34533 

(5) Funds from the replacement 

reserve account cannot be used to pay 

any fees associated with the Section 538 

GRRH loan guarantee, as determined by 

the Agency. 

* * * * * 

Dated: May 18, 2015. 

Tony Hernandez, 

Administrator, Rural Housing Service. 

[FR Doc. 2015–14783 Filed 6–16–15; 8:45 am] 

BILLING CODE 3410–XV–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. FAA–2014–1079; Special 

Conditions No. 25–585–SC] 

Special Conditions: Gulfstream Model 

GVII Series Airplanes; Limit Pilot 

Forces for Side-Stick Controller 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special conditions. 

SUMMARY: These special conditions are 

issued for the Gulfstream Model GVII– 

G500 (GVII series) airplanes. These 

airplanes will have a novel or unusual 

design feature when compared to the 

state of technology envisioned in the 

airworthiness standards for transportcategory airplanes. 

This design feature is associated with 

side-stick controllers that require 

limited pilot force because they are 

operated by one hand only. The 

applicable airworthiness regulations do 

not contain adequate or appropriate 

safety standards for this design feature. 

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: Effective July 17, 2015. 

FOR FURTHER INFORMATION CONTACT: 

Todd Martin, FAA, Airframe and Cabin 

Safety Branch, ANM–115, Transport 

Airplane Directorate, Aircraft 

Certification Service, 1601 Lind Avenue 

SW., Renton, Washington, 98057–3356; 

telephone 425–227–1178; facsimile 

425–227–1320. 

SUPPLEMENTARY INFORMATION: 

Background 

On March 29, 2012, Gulfstream 

Aerospace applied for a type certificate 

for their new Model GVII–G500 

airplane. 

The Model GVII series airplanes are 

large-cabin business jets capable of 

accommodating up to 19 passengers. 

The GVII series will certify a base 

configuration GVII–G500, which 

incorporates a low, swept-wing design 

with winglets and a T-tail. The airplanes 

have two aft-fuselage-mounted Pratt & 

Whitney turbofan engines. Avionics 

include four primary display units and 

multiple touchscreen controllers. The 

flight-control system is a three-axis, flyby-wire system using active control/

coupled side sticks. 

The GVII–G500 has a wingspan of 87 

ft. and a length of 91 ft. Maximum 

takeoff weight is 76,850 lbs. Maximum 

takeoff thrust is 15,135 lbs., maximum 

range is 5,000 nautical miles (nm), and 

maximum operating altitude is 

51,000 ft. 

The Model GVII series airplanes are 

equipped with two side-stick controllers 

instead of the conventional control 

columns and wheels. This side-stick 

controller is designed for one-hand 

operation. The requirement of Title 14, 

Code of Federal Regulations (14 CFR) 

25.397(c), which defines limit pilot 

forces and torques for conventional 

wheel or stick controls, is not adequate 

for a side-stick controller. Special 

conditions are necessary to specify the 

appropriate loading conditions for this 

controller design. 

Type-Certification Basis 

Under the provisions of Title 14, Code 

of Federal Regulations (14 CFR) 21.17, 

Gulfstream must show that the Model 

GVII–G500 airplane meets the 

applicable provisions of 14 CFR part 25, 

as amended by Amendments 25–1 

through 25–137. 

The certification basis of the GVII– 

G500 airplane is 14 CFR part 25, 

effective February 1, 1965, including 

Amendments 25–1 through 25–137; 14 

CFR part 34, as amended by 

Amendments 34–1 through the most 

current amendment at the time of design 

approval; and 14 CFR part 36, 

Amendment 36–29. In addition, the 

certification basis includes special 

conditions and equivalent-safety 

findings related to the flight-control 

system. 

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 Model GVII series airplanes 

because of a novel or unusual design 

feature, special conditions are 

prescribed under § 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 or similar 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 GVII series 

airplanes must comply with the fuelvent and exhaust-emission requirements 

of 14 CFR part 34, and the noisecertification requirements of 14 CFR 

part 36. The FAA must issue a finding 

of regulatory adequacy under § 611 of 

Public Law 92–574, the ‘‘Noise Control 

Act of 1972.’’ 

The FAA issues special conditions, as 

defined in 14 CFR 11.19, under § 11.38, 

and they become part of the typecertification basis under § 21.17(a)(2) for 

new type certificates, and § 21.101 for 

amended type certificates. 

Novel or Unusual Design Features 

The Gulfstream Model GVII series 

airplanes will incorporate the following 

novel or unusual design feature: 

A side-stick controller for one-hand 

operation requiring wrist motion only, 

not arms. 

Discussion 

Current regulations reference piloteffort loads for the flight deck pitch-androll controls that are based on twohanded effort. Special conditions are 

required for the Gulfstream Model GVII 

series airplanes based on similar 

airplane programs that include sidestick controllers. These special 

conditions are also appropriate for the 

Model GVII series airplane’s side-stick 

controller. 

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. 

Discussion of Comments 

Notice of proposed special conditions 

no. 25–15–01–SC for the Gulfstream 

Model GVII series airplanes was 

published in the Federal Register on 

February 26, 2015 (80 FR 10422). No 

substantive comments were received, 

and the special conditions are adopted 

as proposed. 

Applicability 

As discussed above, these special 

conditions apply to Gulfstream Model 

GVII series airplanes. Should 

Gulfstream apply later for a change to 

the type certificate to include another 

model incorporating the same or similar 

novel or unusual design feature, these 

special conditions would apply to that 

model as well. 


srobinson on DSK5SPTVN1PROD with RULES
34534 Federal Register / Vol. 80, No. 116 / Wednesday, June 17, 2015 / Rules and Regulations 

Conclusion 

This action affects only certain novel 

or unusual design features on the 

Gulfstream Model GVII series airplanes. 

It is not a rule of general applicability. 

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, in lieu of 

§ 25.397(c), as part of the typecertification basis. 

For Gulfstream Model GVII series 

airplanes equipped with side-stick 

controls designed for forces to be 

applied by one wrist and not arms, the 

limit pilot forces are as follows. 

1. For all components between and 

including the side-stick controlassembly handle and its control stops: 

Pitch Roll 

Nose up, 200 lbf ....... Nose left, 100 lbf. 

Nose down, 200 lbf ... Nose right, 100 lbf. 

2. For all other components of the 

side-stick control assembly, but 

excluding the internal components of 

the electrical sensor assemblies, to avoid 

damage to the control system as the 

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 June 2, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–14904 Filed 6–16–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–23706; Directorate 

Identifier 2006–NE–03–AD; Amendment 39– 

18177; AD 2014–12–04] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. Turboprop Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2006–15– 

08 for all Honeywell International Inc. 

TPE331–1, –2, –2UA, –3U, –3UW, –5, 

–5A, –5AB, –5B, –6, –6A, –10, –10AV, 

–10GP, –10GT, –10P, –10R, –10T, –10U, 

–10UA, –10UF, –10UG, –10UGR, 

–10UR, –11U, –12JR, –12UA, –12UAR, 

and –12UHR turboprop engines with 

certain Honeywell part numbers (P/Ns) 

of Woodward fuel control unit (FCU) 

assemblies, installed. AD 2006–15–08 

required initial and repetitive 

dimensional inspections of the fuel 

control drives for wear, and replacement 

of the FCU and fuel pump. This new AD 

requires initial and repetitive 

dimensional inspections of the affected 

fuel control drives and insertion of 

certain airplane operating procedures 

into the applicable flight manuals. This 

AD was prompted by reports of loss of 

the fuel control drive, leading to engine 

overspeed, overtorque, overtemperature, 

uncontained rotor failure, and 

asymmetric thrust in multi-engine 

airplanes. We are issuing this AD to 

prevent failure of the fuel control drive 

that could result in damage to the 

engine and airplane. 

DATES: This AD is effective July 22, 

2015. 

ADDRESSES: For service information 

identified in this AD, contact Honeywell 

International Inc., 111 S 34th Street, 

Phoenix, AZ 85034–2802; phone: 800– 

601–3099; Internet: https://

myaerospace.honeywell.com/wps/

portal/!ut/. You may view this service 

information at the FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

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–2006– 

23706; 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 

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 FURTHER INFORMATION CONTACT: 

Joseph Costa, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; phone: 562–627–5246; fax: 

562–627–5210; email: joseph.costa@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2006–15–08, 

Amendment 39–14688 (71 FR 41121, 

July 20, 2006), (‘‘AD 2006–15–08’’). AD 

2006–15–08 applied to all Honeywell 

International Inc. TPE331–1, –2, –2UA, 

–3U, –3UW, –5, –5A, –5AB, –5B, –6, 

–6A, –10, –10AV, –10GP, –10GT, –10P, 

–10R, –10T, –10U, –10UA, –10UF, 

–10UG, –10UGR, –10UR, –11U, –12JR, 

–12UA, –12UAR, and –12UHR 

turboprop engines with certain 

Honeywell part numbers (P/Ns) of 

Woodward FCU assemblies, installed. 

The NPRM published in the Federal 

Register on March 19, 2014 (79 FR 

15261). The NPRM was prompted by 

reports of loss of the fuel control drive, 

leading to engine overspeed, overtorque, 

overtemperature, uncontained rotor 

failure, and asymmetric thrust in multiengine airplanes. The NPRM proposed 

to continue to require initial and 

repetitive dimensional inspections of 

the affected fuel control drives but 

would no longer require the installation 

of a modified FCU. The NPRM also 

proposed to require insertion of certain 

airplane operating procedures into the 

applicable flight manuals. We are 

issuing this AD to prevent failure of the 

fuel control drive that could result in 

damage to the engine and airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 15261, 

March 19, 2014) and the FAA’s response 

to each comment. 


srobinson on DSK5SPTVN1PROD with RULES