Federal Register / Vol. 74, No. 203 / Thursday, October 22, 2009 / Rules and Regulations 54457 

3.5.3.4 Wireless Control Signal. The 

power supplied to a ballast using a wireless 

signal is not easily measured, but is 

estimated to be well below 1.0 watt. 

Therefore, the wireless control signal power 

is not measured as part of this test procedure. 

[FR Doc. E9–25325 Filed 10–21–09; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. NM408; Special Conditions No. 

25–391–SC] 

Special Conditions: Alenia Model C– 

27J Airplane; Liquid Oxygen System 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special conditions. 

SUMMARY: These special conditions are 

issued for the Alenia Model C–27J 

airplane. This airplane will have novel 

or unusual design features when 

compared to the state of technology 

described in the airworthiness standards 

for transport-category airplanes. These 

design features include a liquid-oxygen 

(LOX) system. The applicable 

airworthiness regulations do not contain 

adequate or appropriate safety standards 

for oxygen systems that use liquid 

oxygen. 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 Date: November 23, 

2009. 

FOR FURTHER INFORMATION CONTACT: Tom 

Groves, FAA, International Branch, 

ANM–116, Transport Airplane 

Directorate, Aircraft Certification 

Service, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; 

telephone (425) 227–1503, facsimile 

(425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Background 

On March 27, 2006, the European 

Aviation Safety Agency (EASA) 

forwarded to the FAA an application 

from Alenia Aeronautica of Torino, 

Italy, for U.S. type certification of a 

twin-engine commercial transport 

designated as the Model C–27J. The 

C–27J is a twin-turbopropeller, cargotransport aircraft with a maximum 

takeoff weight of 30,500 kilograms. 

Type Certification Basis 

Under the provisions of section 21.17 

of Title 14, Code of Federal Regulations 

(14 CFR) and the bilateral agreement 

between the U.S. and Italy, Alenia 

Aeronautica must show that the C–27J 

meets the applicable provisions of 14 

CFR part 25, as amended by 

Amendments 25–1 through 25–87. 

Alenia also elects to comply with 

Amendment 25–122, effective 

September 5, 2007, for 14 CFR 25.1317. 

If the Administrator finds that 

existing airworthiness regulations do 

not adequately or appropriately address 

safety standards for the C–27J due to a 

novel or unusual design feature, the 

FAA prescribes special conditions 

under provisions of 14 CFR 21.16. 

In addition to the applicable 

airworthiness regulations and special 

conditions, the C–27J 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, and the FAA must issue a 

finding of regulatory adequacy pursuant 

to § 611 of Public Law 92–574, the 

‘‘Noise Control Act of 1972.’’ 

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 

§ 21.17(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 or similar novel 

or unusual design feature, the special 

conditions also apply to the other model 

under § 21.101. 

Novel or Unusual Design Features 

The Alenia Model C–27J incorporates 

a liquid-oxygen system, including a 

liquid-oxygen converter, valves, 

evaporating coils, lines, regulators, 

indicators, fittings, etc. The existing 

airworthiness regulations do not 

adequately or appropriately address 

safety standards for the design and 

installation of oxygen systems that 

utilize liquid oxygen. These special 

conditions for the C–27J 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 for these novel 

or unusual design features. 

Discussion 

There are no specific regulations that 

address the design and installation of 

oxygen systems that utilize liquid 

oxygen for storage. Existing 

requirements, such as §§ 25.1309, 

25.1441(b) and (c), 25.1451, and 

25.1453, in the Alenia C–27J 

certification basis, provide some design 

standards for crew and medical-oxygensystem installations. However, 

additional design standards for oxygen 

systems utilizing liquid oxygen are 

needed to supplement the existing 

applicable requirements. The quantity 

of liquid oxygen involved in this 

installation and the potential for 

hazards that may result when the 

oxygen content of an enclosed area 

becomes too high because of system 

leaks, malfunction, or damage from 

external sources, make it necessary to 

assure adequate safety standards are 

applied to the design and installation of 

the system in Alenia C–27J airplanes. 

These special conditions require Alenia 

to preclude or minimize the risk of these 

potential hazards. These special 

conditions are also intended to assure 

the safe operation of the liquid-oxygen 

system, and therefore require that: 

• Adequate gaseous oxygen is 

available at temperatures appropriate for 

breathing; 

• The liquid-oxygen converter and 

gaseous-oxygen-distribution lines are 

installed in locations that minimize 

their potential for damage; 

• The quantity of available oxygen is 

clearly indicated to the flight crew; 

• The system is designed to prevent 

leakage of oxygen into the cabin; 

• Condensation from the system is 

collected and drained overboard; 

• The system must be protected from 

possible ignition sources and structural 

damage; and 

• Appropriate maintenance and 

operational instructions are provided to 

ensure the system’s safe operation. 

Taken together, these requirements 

would ensure that this liquid-oxygen 

system provides an equivalent level of 

safety to traditional oxygen systems. 

Discussion of Comments 

Notice of proposed special conditions 

no. 25–09–04–SC for the Alenia model 

C–27J airplane was published in the 

Federal Register on July 13, 2009. No 

comments were received, and the 

special conditions are adopted as 

proposed. 

Applicability 

As discussed above, these special 

conditions are applicable to the Alenia 

C–27J. Should Alenia apply at a later 

date for a change to the type certificate 

to include another airplane model 

incorporating the same novel or unusual 

design features, these special conditions 

apply to that model as well under 

§ 21.101. 


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54458 Federal Register / Vol. 74, No. 203 / Thursday, October 22, 2009 / Rules and Regulations 

Conclusion 

This action affects only certain novel 

or unusual design features of the Alenia 

C–27J. It is not a rule of general 

applicability, and it affects only the 

applicant that applied to the FAA for 

approval of these features on the 

airplane. 

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 the C–27J airplane. 

General 

1. The liquid-oxygen system must be 

located to minimize the possibility of 

exposure of occupants to liquid oxygen 

from a leak or condensation. 

2. The liquid-oxygen converter must 

be located in the airplane so that there 

is no risk of damage to the converter due 

to an uncontained rotor or propellerblade failure. 

3. The liquid-oxygen system’s 

associated gaseous-oxygen-distribution 

lines should be designed and located to 

minimize the hazard from uncontained 

rotor or propeller-blade debris. 

4. The flight-deck oxygen system must 

meet the supply requirements of part 

121 in the event the oxygen-distribution 

line is severed by a rotor or propellerblade fragment. 

5. The pressure-relief valves on the 

liquid-oxygen converters must be 

vented overboard. The ventilation 

means must be configured such that 

liquid and gaseous oxygen will be 

exhausted so that oxygen will not 

accumulate inside the airplane. Means 

must be provided to prevent 

hydrocarbon-fluid migration from 

impinging upon the vent outlet of the 

liquid-oxygen system. 

6. The system must include 

provisions to ensure complete 

conversion of the liquid oxygen to 

gaseous oxygen. The resultant oxygen 

gas must be delivered to the first oxygen 

outlet for breathing such that the 

temperature is no more than 35°F less 

than the cabin ambient temperature or 

32°F (whichever is greater), under the 

conditions of the maximum demand or 

flow of oxygen gas for normal use of the 

oxygen system. A liquid-oxygen shutoff 

valve must be installed on the main 

oxygen-distribution line prior to any 

secondary lines. The shutoff valve must 

be both compatible with liquid-oxygen 

temperatures and readily accessible 

(either directly if manual, or by remote 

activation if automatic). 

7. If multiple converters are used, the 

design should ensure that a leak in one 

converter does not result in leakage of 

oxygen from any other converter. 

8. Approved flexible hoses must be 

used for the airplane-systems 

connections to shock-mounted 

converters, where movement relative to 

the airplane may occur. 

9. Condensation from system 

components or lines must be collected 

by drip pans, shields, or other suitable 

collection means, and drained 

overboard through a drain fitting 

separate from the liquid-oxygen vent 

fitting, as specified in special condition 

5, above. 

10. Oxygen-system components must 

be burst-pressure tested to 3.0 times, 

and proof-pressure tested to 1.5 times, 

the maximum normal operating 

pressure. Compliance with the 

requirement for burst testing may be 

shown by similarity analysis, or a 

combination of similarity analysis and 

test. 

11. Oxygen-system components must 

be electrically bonded to the airplane 

structure. 

12. All gaseous or liquid-oxygen 

connections located in close proximity 

to an ignition source must be shrouded 

and vented overboard using the system 

specified in special condition 5, above. 

13. A means must be provided to 

indicate to the flight crew the quantity 

of available oxygen. 

14. Instructions for Continued 

Airworthiness (ICA) per § 25.1529 must 

be provided for the safe operation and 

maintenance of the liquid-oxygen 

system. 

15. Emergency procedures must be 

developed for the aircraft crew to 

address aircraft-safety-related 

malfunctions of the liquid-oxygen 

system. 

16. The liquid-oxygen-system 

equipment, including the tank, must be 

retained under all loads up to those 

specified in § 25.561(b)(3). The tank 

must be able to resist rupture and to 

retain the liquid oxygen, under the 

inertia forces prescribed for the 

emergency-landing conditions in 

§ 25.561. In addition, the tank must be 

able to withstand, without failure, the 

vibration, inertia, fluid, and structural 

loads that it may be subjected to in 

operation. The liquid-oxygen 

components, including the tank, must 

be protected from scraping or impact 

from baggage, cargo, or other contents. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–25396 Filed 10–21–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

14 CFR Part 97 

[Docket No. 30691; Amdt. No. 3343] 

Standard Instrument Approach 

Procedures, and Takeoff Minimums 

and Obstacle Departure Procedures; 

Miscellaneous Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This rule establishes, amends, 

suspends, or revokes Standard 

Instrument Approach Procedures 

(SIAPs) and associated Takeoff 

Minimums and Obstacle Departure 

Procedures for operations at certain 

airports. These regulatory actions are 

needed because of the adoption of new 

or revised criteria, or because of changes 

occurring in the National Airspace 

System, such as the commissioning of 

new navigational facilities, adding new 

obstacles, or changing air traffic 

requirements. These changes are 

designed to provide safe and efficient 

use of the navigable airspace and to 

promote safe flight operations under 

instrument flight rules at the affected 

airports. 

DATES: This rule is effective October 22, 

2009. The compliance date for each 

SIAP, associated Takeoff Minimums, 

and ODP is specified in the amendatory 

provisions. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of October 22, 

2009. 

ADDRESSES: Availability of matter 

incorporated by reference in the 

amendment is as follows: 

For Examination 

1. FAA Rules Docket, FAA 

Headquarters Building, 800 

Independence Avenue, SW., 

Washington, DC 20591; 

2. The FAA Regional Office of the 

region in which the affected airport is 

located; 

3. The National Flight Procedures 

Office, 6500 South MacArthur Blvd., 

Oklahoma City, OK 73169 or 


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