34242 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations 

no extraordinary circumstances creating 

the potential for significant 

environmental effects. Therefore, this 

rule is categorically excluded from 

further NEPA review. 

List of Subjects in 8 CFR Part 293 

Administrative practice and 

procedure, Aliens, Bonds, Immigration, 

Interest rate. 

Amendments to the Regulations 

For the reasons discussed in the 

preamble, DHS amends 8 CFR part 293 

as follows: 

PART 293—DEPOSIT OF AND 

INTEREST ON CASH RECEIVED TO 

SECURE IMMIGRATION BONDS 

■ 1. Revise the authority citation for part 

293 to read as follows: 

Authority: 8 U.S.C. 1363. 

■ 2. Revise § 293.1 to read as follows: 

§ 293.1 Computation of interest. 

The Secretary of the Treasury 

determines the rate at which an 

immigration bond secured by cash shall 

bear interest, consistent with 8 CFR 

293.2. Interest shall be computed from 

the deposit date to and including the 

refund date or breach date of the 

immigration bond. For purposes of this 

part, the deposit date shall be the date 

shown on the receipt for the cash 

received as security on an immigration 

bond. The refund date shall be the date 

upon which the interest is certified to 

the Treasury Department for payment. 

The breach date shall be the date the 

immigration bond was breached as 

shown on Form I–323—‘‘Notice— 

Immigration Bond Breached.’’ In 

counting the number of days for which 

interest shall be computed, the day on 

which the cash was deposited shall not 

be counted; however, the refund date or 

the breach date shall be counted. 

■ 3. Revise § 293.2 to read as follows: 

§ 293.2 Interest rate. 

Interest on cash deposited to secure 

immigration bonds will be at the rate as 

determined by the Secretary of the 

Treasury, but in no case will exceed 3 

per centum per annum or be less than 

zero. The rate will be published by 

Treasury on the Treasury Web site or 

through another mechanism. 

■ 4. Revise § 293.3 to read as follows: 

§ 293.3 Time of payment. 

Interest shall be paid only at time of 

disposition of principal cash when the 

immigration bond has been cancelled or 

declared breached. 

§ 293.4 [Removed] 

■ 5. Remove § 293.4. 

Jeh Charles Johnson, 

Secretary of Homeland Security. 

[FR Doc. 2015–14675 Filed 6–15–15; 8:45 am] 

BILLING CODE 9111–28–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 23 

[Docket No. FAA–2015–0722; Special 

Conditions No. 23–265–SC] 

Special Conditions: Honda Aircraft 

Company, Model HA–420; Fire 

Extinguishing for Overwing Pylon 

Mounted Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special conditions; request 

for comments. 

SUMMARY: These special conditions are 

issued for the Honda Aircraft Company 

model HA–420 airplane. This airplane 

will have a novel or unusual design 

feature associated with mounting the 

engines on the wings in close proximity 

to the aft fuselage. 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: The effective date of these 

special conditions is June 16, 2015. 

We must receive your comments by 

July 16, 2015. 

ADDRESSES: Send comments identified 

by docket number FAA–2015–0722 

using any of the following methods: 

D Federal eRegulations Portal: Go to 

http://www.regulations.gov and follow 

the online instructions for sending your 

comments electronically. 

D 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. 

D Hand Delivery of 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. 

D Fax: Fax comments to Docket 

Operations at 202–493–2251. 

Privacy: The FAA will post all 

comments it receives, without change, 

to http://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 the 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: Jeff 

Pretz, Federal Aviation Administration, 

Aircraft Certification Service, Small 

Airplane Directorate, ACE–111, 901 

Locust, Kansas City, Missouri 64106; 

816–329–3239, fax 816–329–4090, email 

jeff.pretz@faa.gov. 

SUPPLEMENTARY INFORMATION: The FAA 

has determined, in accordance with 5 

U.S.C. 553(b)(3)(B) and (d)(3), that 

notice and opportunity for prior public 

comment hereon are unnecessary 

because the substance of these special 

conditions has been subject to the 

public comment process in several prior 

instances with no substantive comments 

received. The FAA therefore finds that 

good cause exists for making these 

special conditions effective upon 

issuance. 

Special condition 

No. Company/Airplane Model 

23–210–SC ....... Adam Aircraft Model A700. 

23–245–SC ....... Cirrus Design Corporation 

Model SF50. 

23–221–SC ....... Embraer S.A. Model EMB– 

500. 

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 ask that you send 

us two copies of written comments. 

We will consider all comments we 

receive on or before the closing date for 

comments. We will consider comments 


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Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations 34243 

filed late if it is possible to do so 

without incurring expense or delay. We 

may change these special conditions 

based on the comments we receive. 

Background 

On October 11, 2006, Honda Aircraft 

Company applied for a type certificate 

for their new model HA–420. On 

October 10, 2013, Honda Aircraft 

Company requested an extension with 

an effective application date of October 

1, 2013. This extension changed the 

type certification basis to amendment 

23–62. 

The HA–420 is a four to five 

passenger (depending on configuration), 

two crew, lightweight business jet with 

a 43,000-foot service ceiling and a 

maximum takeoff weight of 9963 

pounds. The airplane is powered by two 

GE-Honda Aero Engines (GHAE) HF– 

120 turbofan engines. 

The turbofan engines are mounted on 

a single pylon on each wing near the aft 

fuselage. These types of aft mounted 

engine installations, along with the need 

to protect such installed engines from 

fires, were not envisioned in the 

development of the part 23 normal 

category regulations. The performance 

of the airplane is such that a pilot may 

not be able to locate a suitable landing 

site and safely land the airplane prior to 

a fire escaping the fire containment 

capabilities of the engine fire zone. 

Type Certification Basis 

Under the provisions of 14 CFR 21.17, 

Honda Aircraft Company must show 

that the model HA–420 meets the 

applicable provisions of part 23, as 

amended by Amendment 23–1 through 

Amendment 23–62 thereto. 

If the Administrator finds that the 

applicable airworthiness regulations 

(i.e., 14 CFR part 23) do not contain 

adequate or appropriate safety standards 

for the model HA–420 because of a 

novel or unusual design feature, special 

conditions are prescribed under the 

provisions of § 21.16. 

In addition to the applicable 

airworthiness regulations and special 

conditions, the model HA–420 must 

comply with the fuel vent and exhaust 

emission requirements of 14 CFR part 

34 and the noise certification 

requirements of 14 CFR part 36. In 

addition, the FAA must issue a finding 

of regulatory adequacy under section 

611 of Public Law 92–574, the ‘‘Noise 

Control Act of 1972.’’ 

The FAA issues special conditions, as 

defined in § 11.19, under § 11.38 and 

they become part of the type 

certification basis under § 21.17(a)(2). 

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, the special conditions 

would also apply to the other model. 

Novel or Unusual Design Features 

The model HA–420 will incorporate 

the following novel or unusual design 

features: Turbofan engines are mounted 

on a single pylon on each wing near the 

aft fuselage not in the pilot’s line of 

sight. 

This type of configuration was not 

envisioned in the development of part 

23 normal category airplanes. Therefore, 

a special condition for the engine fire 

extinguishing system on the model HA– 

420 is required. 

As the extinguishing agent is subject 

to change during the service life of the 

airplane, the certification basis must 

include SC 23.1195, SC 23.1197, SC 

23.1199, and SC 23.1201 in their 

entirety. 

Discussion 

Part 23 has historically addressed fire 

protection through prevention, 

identification, and containment. 

Prevention has been accomplished by 

minimizing the potential for ignition of 

flammable fluids and vapors. 

Identification has traditionally been 

achieved by the location of the engines 

within the pilot’s primary field of view 

and/or with the incorporation of fire 

detection systems. This philosophy has 

provided for both the rapid detection of 

a fire and confirmation when it has been 

extinguished. Containment has been 

provided through the isolation of 

designated fire zones through flammable 

fluid shutoff valves and firewalls. The 

containment philosophy also ensures 

components of the engine control 

system will function effectively to 

permit a safe shutdown of the engine. 

However, containment has only been 

required to be demonstrated for 15 

minutes. In the event of a fire in a 

traditional part 23 airplane, the 

corrective action is to land as soon as 

possible. For a small, simple aircraft 

originally envisioned by part 23, it is 

possible to descend the aircraft to a 

suitable landing site within 15 minutes. 

Thus, if the isolation means do not 

extinguish the fire, the occupants can 

safely exit the aircraft prior to breaching 

the firewall. These simple and 

traditional aircraft normally have the 

engine located away from critical flight 

control systems and primary structure. 

This has ensured that throughout the 

fire event the pilot can maintain control 

and continue safe flight. It has also 

made predicting the effects of a fire 

relatively easy. Other design features of 

these simple and traditional aircraft, 

such as low stall speeds and short 

landing distances, ensure that even in 

the event of an off field landing the 

potential for a catastrophic outcome has 

been minimized. 

Amendment 23–62 applies to the 

model HA–420 and addresses the 

concerns above by requiring engine fire 

extinguishing for engines embedded in 

the fuselage or in pylons on the aft 

fuselage, but do not address engines 

mounted in pylons over the wing as 

used on the model HA–420. The engine 

fire concerns for engines mounted in 

overwing pylons near the aft fuselage 

are the same as those associated with 

engines mounted in pylons on the aft 

fuselage; therefore, the engine fire 

extinguishing requirements included in 

part 23, amendments 23–1 through 23– 

62 apply. 

Applicability 

As discussed above, these special 

conditions are applicable to the model 

HA–420. Should Honda Airplane 

Company apply at a later date for a 

change to the type certificate to include 

another model incorporating the same 

novel or unusual design feature, the 

special conditions would apply to that 

model as well. 

Conclusion 

This action affects only certain novel 

or unusual design features on one model 

of airplanes. It is not a rule of general 

applicability and affects only the 

applicant who applied to the FAA for 

approval of these features on the 

airplane. 

The substance of these special 

conditions has been subjected to the 

notice and comment period in several 

prior instances, identified above, 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, notice and opportunity for 

prior public comment hereon are 

unnecessary and the FAA finds good 

cause, in accordance with 5 U.S.C. 

553(b)(3)(B) and (d)(3), making these 

special conditions effective upon 

issuance. 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 23 

Aircraft, Aviation safety, Signs and 

symbols. 


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34244 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations 

Citation 

The authority citation for these 

special conditions is as follows: 

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

44701; 14 CFR 21.16 and 21.17; and 14 CFR 

11.38 and 11.19. 

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 Honda Airplane Company 

model HA–420 airplanes. 

1. Fire Extinguishing for Overwing 

Pylon Mounted Engines 

SC 23.1195 Fire Extinguishing 

Systems 

(a) Fire extinguishing systems must be 

installed and compliance shown with 

the following: 

(1) Except for combustor, turbine, and 

tailpipe sections of turbine-engine 

installations that contain lines or 

components carrying flammable fluids 

or gases for which a fire originating in 

these sections is shown to be 

controllable, a fire extinguisher system 

must serve each engine compartment. 

(2) The fire extinguishing system, the 

quantity of the extinguishing agent, the 

rate of discharge, and the discharge 

distribution must be adequate to 

extinguish fires. An individual ‘‘oneshot’’ system may be used except for 

embedded engines where a ‘‘two shot’’ 

system must be used. 

(3) The fire extinguishing system for 

a nacelle must be able to simultaneously 

protect each compartment of the nacelle 

for which protection is provided. 

(b) If an auxiliary power unit is 

installed in any airplane certificated to 

this part, that auxiliary power unit 

compartment must be served by a fire 

extinguishing system meeting the 

requirements of paragraph (a)(2) of this 

section. 

SC 23.1197 Fire Extinguishing Agents 

The following applies: 

(a) Fire extinguishing agents must— 

(1) Be capable of extinguishing flames 

emanating from any burning of fluids or 

other combustible materials in the area 

protected by the fire extinguishing 

system; and 

(2) Have thermal stability over the 

temperature range likely to be 

experienced in the compartment in 

which they are stored. 

(b) If any toxic extinguishing agent is 

used, provisions must be made to 

prevent harmful concentrations of fluid 

or fluid vapors (from leakage during 

normal operation of the airplane or as a 

result of discharging the fire 

extinguisher on the ground or in flight) 

from entering any personnel 

compartment, even though a defect may 

exist in the extinguishing system. This 

must be shown by test except for builtin carbon dioxide fuselage compartment 

fire extinguishing systems for which— 

(1) Five pounds or less of carbon 

dioxide will be discharged, under 

established fire control procedures, into 

any fuselage compartment; or 

(2) Protective breathing equipment is 

available for each flight member on 

flight deck duty. 

SC 23.1199 Extinguishing Agent 

Containers 

The following applies: 

(a) Each extinguishing agent container 

must have a pressure relief valve to 

prevent bursting of the container by 

excessive internal pressures. 

(b) The discharge end of each 

discharge line from a pressure relief 

connection must be located so that 

discharge of the fire-extinguishing agent 

would not damage the airplane. The line 

must also be located or protected to 

prevent clogging caused by ice or other 

foreign matter. 

(c) A means must be provided for 

each fire extinguishing agent container 

to indicate that the container has 

discharged or that the charging pressure 

is below the established minimum 

necessary for proper functioning. 

(d) The temperature of each container 

must be maintained under intended 

operating conditions, to prevent the 

pressure in the container from— 

(1) Falling below that necessary to 

provide an adequate rate of discharge; or 

(2) Rising high enough to cause 

premature discharge. 

(e) If a pyrotechnic capsule is used to 

discharge the extinguishing agent, each 

container must be installed so that 

temperature conditions will not cause 

hazardous deterioration of the 

pyrotechnic capsule. 

SC 23.1201 Fire Extinguishing System 

Materials 

The following apply: 

(a) No material in any fire 

extinguishing system may react 

chemically with any extinguishing agent 

so as to create a hazard. 

(b) Each system component in an 

engine compartment must be fireproof. 

Issued in Kansas City, Missouri, on June 9, 

2015. 

Earl Lawrence, 

Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2015–14816 Filed 6–15–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0575; Directorate 

Identifier 2014–NM–086–AD; Amendment 

39–18181; AD 2015–12–07] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 747–8F and 

747–8 series airplanes. This AD was 

prompted by reports of delamination 

damage to leading edge (LE) variable 

camber krueger (VCK) flaps. This AD 

requires repetitive inspections to detect 

delamination damage of the lightning 

strike applique (LSA) on certain LE VCK 

flaps, and corrective actions if 

necessary. We are issuing this AD to 

detect and correct delamination damage 

to certain LE VCK flaps, which can 

reduce the lightning strike protection 

capability on certain LE VCK flaps and 

result in an uncommanded motion of 

the trailing edge flap system; such 

uncommanded flap motion, without 

shutdown of the trailing edge or leading 

edge flaps, could cause unexpected 

changes in lift, potentially resulting in 

asymmetric lift and loss of control of the 

airplane. 

DATES: This AD is effective July 21, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 21, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.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 2014– 

0575. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://


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