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Rules and Regulations Federal Register

56343 

Vol. 70, No. 186 

Tuesday, September 27, 2005 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. NM304; Special Conditions No. 

25–299–SC] 

Special Conditions: Airbus Model A318 

Airplanes Equipped With Pratt and 

Whitney PW6000 Engines; Sudden 

Engine Stoppage 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special conditions. 

SUMMARY: These special conditions are 

issued for the Airbus Model A318–121 

and A318–122 airplanes equipped with 

Pratt and Whitney PW6000 engines. 

These airplanes will have novel or 

unusual design features when compared 

to the state of technology envisioned in 

the airworthiness standards for 

transport category airplanes, associated 

with engine size and torque load, which 

affect sudden engine stoppage. 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. 

EFFECTIVE DATE: October 27, 2005. 

FOR FURTHER INFORMATION CONTACT: Tim 

Dulin, FAA, International Branch, 

ANM–116, Transport Airplane 

Directorate, Aircraft Certification 

Service, 1601 Lind Avenue SW., 

Renton, Washington 98055–4056; 

telephone (425) 227–2141; facsimile 

(425) 227–1232. 

SUPPLEMENTARY INFORMATION: 

Background 

On December 22, 1998, Airbus 

submitted an application to the FAA to 

amend Type Certificate No. A28NM to 

include the new Model A318 airplane 

equipped with Pratt and Whitney 

PW6000 engines (Model A318–121 and 

A318–122) or with optional CFMI 

CFM56 engines (Model A318–111 and 

A318–112). On May 14, 2002, Airbus 

applied for extension of the application 

for the Model A318 airplanes equipped 

with PW6000 engines and selected a 

new reference date of application of 

November 15, 2001. 

The Airbus Model A318 airplane is a 

shortened reduced capacity version of 

the Model A320–200. The Model A318 

will have a maximum passenger 

capacity of 136 versus a maximum 

passenger capacity of 179 for the Model 

A320 series airplanes and 145 for the 

Model A319 series airplanes. The 

fuselage length is reduced by four and 

one half frames (94 inches) compared to 

the Model A319 series airplanes. The 

maximum takeoff weight will be 59,000 

kg (130,000 pounds) with growth 

options to 68,000 kg (150,000 pounds) 

versus maximum takeoff weight range of 

68,000 kg to 77,000 kg for the Model 

A320 series airplanes and 64,000 kg to 

75,500 kg for the Model A319 series 

airplanes. The Model A318 will be 

powered by all new Pratt and Whitney 

PW6000 engines or by CFMI CFM56–5B 

engines all in the 22,000 to 24,000 

pound thrust range. Other changes 

include a new engine/nacelle and pylon 

adaptation for the PW6000 engine 

installation. 

Type Certification Basis 

Under the provisions of 14 Code of 

Federal Regulations (CFR) 21.101, 

Airbus must show that the Model A318 

airplane, equipped with Pratt and 

Whitney PW6000 engines, meets the 

applicable provisions of the regulations 

incorporated by reference in Type 

Certificate No. A28NM or the applicable 

regulations in effect on the date of 

application for the change to the type 

certificate. 

The regulations incorporated by 

reference in the type certificate are 

commonly referred to as the ‘‘original 

type certification basis.’’ 

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 Airbus Model A318 airplane, 

equipped with Pratt and Whitney 

PW6000 engines, 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 Airbus Model A318 

airplane 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. 

Special conditions, as defined in 14 

CFR 11.19, are issued in accordance 

with § 11.38 and become part of the type 

certification basis in accordance with 

§ 21.101. 

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, the special conditions 

would also apply to the other novel 

under the provisions of § 21.101. 

Novel or Unusual Design Features 

The Airbus Model A318 airplane, 

equipped with Pratt and Whitney 

PW6000 engines, will incorporate novel 

or unusual design features involving 

engine size torque load that affect 

sudden engine stoppage conditions. 

Because of rapid improvements in 

airplane technology, the applicable 

airworthiness regulations do not contain 

adequate or appropriate safety standards 

for these design features. The special 

conditions for the Airbus Model A318 

airplane, equipped with Pratt and 

Whitney PW6000 engines, 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. 

Since 1957, Civil Aviation Regulation 

4b.216 and its successors, currently 

§ 25.361(b), have required that engine 

mounts and supporting structures be 

designed to withstand the limit engine 

torque load which is posed by sudden 

engine stoppage due to malfunction or 

structural failure, such as compressor 

jamming. Design torque loads associated 

with typical failure scenarios were 

estimated by the engine manufacturer 

and provided to the airframe 

manufacturer as limit loads. These limit 

loads were considered simple, pure 

56344 Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Rules and Regulations 

static torque loads. However, the size, 

configuration, and failure modes of jet 

engines have changed considerably from 

those envisioned when the engine 

seizure requirement of § 25.361(b) was 

first adopted. Current engines are much 

larger and are now designed with large 

bypass fans capable of producing much 

larger torque, if they become jammed. 

Relative to the engine configurations 

that existed when the rule was 

developed in 1957, the present 

generation of engines is sufficiently 

different and novel to justify issuance of 

special conditions to establish 

appropriate design standards. The latest 

generation of jet engines is capable of 

producing, during failure, transient 

loads that are significantly higher and 

more complex than those produced by 

the generation of engines in existence 

when the current regulation was 

developed. 

In order to maintain the level of safety 

envisioned in § 25.361(b), more 

comprehensive criteria are needed for 

the new generation of high bypass 

engines. The proposed special condition 

would distinguish between the more 

common failure events involving 

transient deceleration conditions with 

temporary loss of thrust capability and 

those rare events resulting from 

structural failures. Associated with 

these events, the proposed criteria 

establish design limit and ultimate load 

conditions. 

Discussion of Comments 

Notice of proposed special conditions 

No. 25–05–03–SC for the Airbus Model 

A318 airplanes equipped with Pratt and 

Whitney PW6000 engines, was 

published in the Federal Register on 

April 11, 2005 (70 CFR 18321). No 

comments were received. However, the 

FAA has reconsidered the inclusion of 

auxiliary power units in these special 

conditions. While § 25.361(b) is 

interpreted to apply to auxiliary power 

units, the novel or unusual design 

features identified above do not apply to 

them. Therefore, auxiliary power units 

are excluded from those special 

conditions and would continue to be 

treated under the current § 25.361(b). 

Except for the removal of auxiliary 

power units, these special conditions 

are adopted as proposed. 

Applicability 

As discussed above, these special 

conditions are applicable to Airbus 

Model A318–121 and A318–122 

airplanes equipped with Pratt and 

Whitney PW6000 engines. Should 

Airbus apply at a later date for a change 

to the type certificate to include other 

type designs incorporating the same 

novel or unusual design feature, these 

special conditions would apply to that 

model as well under the provisions of 

§ 21.101. 

Condition 

This action affects certain novel or 

unusual design features on the Airbus 

Model A318 airplane equipped with 

Pratt and Whitney PW6000 engines. 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 as part of the type 

certification basis for Airbus Model 

A318 airplane equipped with Pratt and 

Whitney PW6000 engines. 

For turbine engine installations other 

than auxiliary power units, in lieu of 

compliance with § 25.361(b), the 

following special condition applies: 

(a) The engine mounts, pylons and 

adjacent supporting airframe structure 

must be designed to withstand 1g level 

flight loads acting simultaneously with 

the maximum limit torque loads 

imposed by each of the following: 

(1) Sudden engine deceleration due to 

a malfunction which could result in a 

temporary loss of power or thrust. 

(2) The maximum acceleration of the 

engine. 

(b) For engine supporting structure, 

an ultimate loading condition must be 

considered that combines 1g flight loads 

with the transient dynamic loads 

resulting from each of the following: 

(1) The loss of any fan, compressor, or 

turbine blade. 

(2) Where applicable to a specific 

engine design, and separately from the 

conditions specified in paragraph (b)(1), 

any other engine structural failure that 

results in higher loads. 

(c) The ultimate loads developed from 

the conditions specified in paragraphs 

(b)(1) and (b)(2) above are to be 

multiplied by a factor of 1.0 when 

applied to engine mounts and pylons 

and multiplied by a factor of 1.25 when 

applied to adjacent supporting airframe 

structure. 

Issued in Renton, Washington, on 

September 14, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–19206 Filed 9–26–05; 8:45 am] 

BILLING CODE 4910–13–M 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22483; Directorate 

Identifier 2004–NM–236–AD; Amendment 

39–14292; AD 2005–19–27] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A330–200 series 

airplanes. This AD requires inspecting 

to determine the serial numbers and 

flight cycles of the fuel jettison valves 

and removing certain valves as 

applicable. This AD also requires doing 

a one-time inspection for cracks of the 

remaining jettison valves and removing 

any cracked valves. This AD also 

requires modifying the diameters of the 

six attachment holes in the wing bottom 

skin panel before installing a new or 

serviceable jettison valve. This AD 

results from reports of fuel leaks in the 

fuel jettison system located on the 

wings. We are issuing this AD to 

prevent fuel leaks from the fuel jettison 

outlets, which could result in fuel 

vapors coming into contact with 

ignition sources, and consequent fire or 

explosion. 

DATES: Effective October 12, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 12, 2005. 

We must receive comments on this 

AD by November 28, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically.