58824 Federal Register / Vol. 69, No. 190 / Friday, October 1, 2004 / Rules and Regulations 

Frequency 

Field strength

(volts per meter) 

Peak Average 

2 MHz–30 MHz ..... 100 100 

30 MHz–70 MHz ... 50 50 

70 MHz–100 MHz 50 50 

100 MHz–200 MHz 100 100 

200 MHz–400 MHz 100 100 

400 MHz–700 MHz 700 50 

700 MHz–1 GHz ... 700 100 

1 GHz–2 GHz ....... 2000 200 

2 GHz–4 GHz ....... 3000 200 

4 GHz–6 GHz ....... 3000 200 

6 GHz–8 GHz ....... 1000 200 

8 GHz–12 GHz ..... 3000 300 

12 GHz–18 GHz ... 2000 200 

18 GHz–40 GHz ... 600 200 

The field strengths are expressed in terms 

of peak root-mean-square (rms) values. 

or, 

(2) The applicant may demonstrate by 

a system test and analysis that the 

electrical and electronic systems that 

perform critical functions can withstand 

a minimum threat of 100 volts per 

meter, electrical field strength, from 10 

kHz to 18 GHz. When using this test to 

show compliance with the HIRF 

requirements, no credit is given for 

signal attenuation due to installation. 

A preliminary hazard analysis must 

be performed by the applicant, for 

approval by the FAA, to identify either 

electrical or electronic systems that 

perform critical functions. The term 

‘‘critical’’ means those functions whose 

failure would contribute to, or cause, a 

failure condition that would prevent the 

continued safe flight and landing of the 

airplane. The systems identified by the 

hazard analysis that perform critical 

functions are candidates for the 

application of HIRF requirements. A 

system may perform both critical and 

non-critical functions. Primary 

electronic flight display systems, and 

their associated components, perform 

critical functions such as attitude, 

altitude, and airspeed indication. The 

HIRF requirements apply only to critical 

functions. 

Compliance with HIRF requirements 

may be demonstrated by tests, analysis, 

models, similarity with existing 

systems, or any combination of these. 

Service experience alone is not 

acceptable since normal flight 

operations may not include an exposure 

to the HIRF environment. Reliance on a 

system with similar design features for 

redundancy as a means of protection 

against the effects of external HIRF is 

generally insufficient since all elements 

of a redundant system are likely to be 

exposed to the fields concurrently. 

Applicability: As discussed above, 

these special conditions are applicable 

to Raytheon Model 200, 300, and B300 

airplanes. Should ARINC, Inc. apply at 

a later date for a supplemental type 

certificate to modify any other model on 

the same type certificate to incorporate 

the same novel or unusual design 

feature, the special conditions would 

apply to that model as well under the 

provisions of § 21.101. 

Conclusion 

This action affects only certain novel 

or unusual design features on the 

models listed. 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 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. For this reason, and 

because a delay would significantly 

affect the certification of the airplane, 

which is imminent, the FAA has 

determined that prior public notice and 

comment are unnecessary and 

impracticable, and good cause exists for 

adopting these special conditions 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.

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 21.101; 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 Raytheon Model 200, 300, and 

B300 airplanes modified by ARINC, Inc. 

to add a digital Air Data computer. 

1. Protection of Electrical and 

Electronic Systems From High Intensity 

Radiated Fields (HIRF). Each system 

that performs critical functions must be 

designed and installed to ensure that the 

operations, and operational capabilities 

of these systems to perform critical 

functions, are not adversely affected 

when the airplane is exposed to high 

intensity radiated electromagnetic fields 

external to the airplane. 

2. For the purpose of these special 

conditions, the following definition 

applies: Critical Functions: Functions 

whose failure would contribute to, or 

cause, a failure condition that would 

prevent the continued safe flight and 

landing of the airplane.

Issued in Kansas City, Missouri on 

September 20, 2004. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–22019 Filed 9–30–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19170; Directorate 

Identifier 2004–NE–18–AD; Amendment 39–

13809; AD 2004–20–04] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada PT6B–36A and PT6B–

36B Turboshaft Engines

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Pratt & 

Whitney Canada (PWC) PT6B–36A and 

PT6B–36B turboshaft engines with 

compressor rear hubs, part number (P/

N) 3018111 installed. This AD requires 

reviewing, and correcting if necessary 

the critical part record for compressor 

rear hubs, P/N 3018111. This AD also 

requires removing compressor rear hubs 

from service that exceed the published 

part life limit, before further flight. This 

AD results from the discovery of a 

compressor rear hub, P/N 3018111, that 

exceeded the published life limit. This 

occurred because the operator used an 

incorrect life limit calculation contained 

in a PWC Service Bulletin. We are 

issuing this AD to prevent uncontained 

failure of the compressor rear hub and 

damage to the airplane.

DATES: Effective October 18, 2004. The 

Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the 

regulations as of October 18, 2004. 

We must receive any comments on 

this AD by November 30, 2004.

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

Federal Register / Vol. 69, No. 190 / Friday, October 1, 2004 / Rules and Regulations 58825

• 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. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

001. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

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

through Friday, except Federal holidays. 

You can get the service information 

identified in this AD from Pratt & 

Whitney Canada, 1000 Marie-Victorin, 

Longueuil, Quebec, Canada J4G1A1. 

This information may be examined at 

the Docket Management Facility; U.S. 

Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

001, on the internet at http://

dms.dot.gov; or at the National Archives 

and Records Administration (NARA). 

For information on the availability of 

this material at NARA, call 202–741–

6030, or go to: http://www.archives.gov/

federal_register/

code_of_federal_regulations/

ibr_locations.html.

You may examine the comments on 

this AD in the AD docket on the Internet 

at http://dms.dot.gov.

FOR FURTHER INFORMATION CONTACT: Ian 

Dargin, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7178; fax 

(781) 238–7199.

SUPPLEMENTARY INFORMATION: Transport 

Canada, which is the airworthiness 

authority for Canada, recently notified 

us that an unsafe condition might exist 

on PWC PT6B–36A and PT6B–36B 

turboshaft engines. Transport Canada 

advises that a compressor rear hub,

P/N 3018111, was discovered that 

exceeded the published life limit. This 

occurred because the operator used an 

incorrect life limit calculation. PWC 

investigated and confirmed that PWC 

Service Bulletin (SB) No. 11002, 

Original issue-through-Revision 7, 

incorrectly listed the Flight Count 

Factor (FCF) of 1 for compressor rear 

hubs, P/N 3018111. The correct FCF for 

that part is 3. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of PWC SB No. 

11002, Revision 8, dated June 11, 2003, 

that provides the service life limit and 

correct FCF for compressor rear hubs

P/N 3018111. Transport Canada 

classified this service bulletin as 

mandatory and issued AD CF–2003–16, 

dated June 27, 2003, to ensure the 

airworthiness of these PT6B–36A and 

PT6B–36B turboshaft engines in 

Canada. 

Bilateral Airworthiness Agreement 

These PWC PT6B–36A and PT6B–36B 

turboshaft engines are manufactured in 

Canada and are type certificated for 

operation in the United States under the 

provisions of section 21.29 of the 

Federal Aviation Regulations (14 CFR 

21.29) and the applicable bilateral 

airworthiness agreement. Under this 

bilateral airworthiness agreement, 

Transport Canada kept the FAA 

informed of the situation described 

above. We have examined the findings 

of Transport Canada, reviewed all 

available information, and determined 

that AD action is necessary for products 

of this type design that are certificated 

for operation in the United States. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other PWC PT6B–36A and PT6B–

36B turboshaft engines of the same type 

design. We are issuing this AD to 

prevent uncontained failure of the 

compressor rear hub and damage to the 

airplane. This AD requires reviewing, 

and correcting if necessary the critical 

part record for compressor rear hubs, P/

N 3018111. This AD also requires 

removing compressor rear hubs from 

service that exceed the published part 

life limit, before further flight. You must 

use the service information described 

previously to perform the actions 

required by this AD. 

FAA’s Determination of the Effective 

Date 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we have found that notice and 

opportunity for public comment before 

issuing this AD are impracticable, and 

that good cause exists for making this 

amendment effective in less than 30 

days.

Docket Management System (DMS) 

We have implemented new 

procedures for maintaining AD dockets 

electronically. As of May 17, 2004, we 

post new AD actions on the DMS and 

assign a DMS docket number. We track 

each action and assign a corresponding 

Directorate identifier. The DMS docket 

No. is in the form ‘‘Docket No. FAA–

200X–XXXXX.’’ Each DMS docket also 

lists the Directorate identifier (‘‘Old 

Docket Number’’) as a cross-reference 

for searching purposes. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

written relevant data, views, or 

arguments regarding this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘AD Docket No. 

FAA–2004–19170; Directorate Identifier 

2004–NE–18–AD’’ in the subject line of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the rule that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http://

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of the DMS web site, 

anyone can find and read the comments 

in any of our dockets, including the 

name of the individual who sent the 

comment (or signed the comment on 

behalf of an association, business, labor 

union, etc.). You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78) or you may visit 

http://dms.dot.gov.

We are reviewing the writing style we 

currently use in regulatory documents. 

We are interested in your comments on 

whether the style of this document is 

clear, and your suggestions to improve 

the clarity of our communications with 

you. You can get more information 

about plain language at http://

www.faa.gov/language and http://

www.plainlanguage.gov.

Examining the AD Docket 

You may examine the docket that 

contains the AD, any comments 

received, and any final disposition in 

person at the DMS Docket Offices 

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

through Friday, except Federal holidays. 

The Docket Office (telephone (800) 647–

5227) is located on the plaza level of the 

Department of Transportation Nassif 

Building at the street address stated in 

ADDRESSES. Comments will be available 

in the AD docket shortly after the DMS 

receives them. 

58826 Federal Register / Vol. 69, No. 190 / Friday, October 1, 2004 / Rules and Regulations 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national Government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary by sending a request to us 

at the address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Under the authority delegated to me by 

the Administrator, the FAA amends part 

39 of the Federal Aviation Regulations 

(14 CFR part 39) as follows:

PART 39—AIRWORTHINESS 

DIRECTIVES

■ 1. The authority citation for part 39 

continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

■ 2. The Federal Aviation 

Administration (FAA) amends § 39.13 by 

adding the following new airworthiness 

directive (AD):

2004–20–04 Pratt & Whitney Canada:

Amendment 39–13809. Docket No. 

FAA–2004–19170; Directorate Identifier 

2004–NE–18–AD. 

Effective Date 

(a) This AD becomes effective October 18, 

2004. 

Affected ADs 

(b) None.

Applicability 

(c) This AD applies to Pratt & Whitney 

Canada (PWC) PT6B–36A and PT6B–36B 

turboshaft engines with compressor rear 

hubs, part number (P/N) 3018111 installed. 

These engines are installed on, but not 

limited to, Sikorsky S–76B helicopters. 

Unsafe Condition 

(d) This AD results from results from the 

discovery of a compressor rear hub, P/N 

3018111, that exceeded the published life 

limit. This occurred because the operator 

used an incorrect life limit calculation 

contained in a PWC Service Bulletin. We are 

issuing this AD to prevent uncontained 

failure of the compressor rear hub and 

damage to the helicopter. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

(f) Within 30 days or at the next engine 

shop visit, whichever occurs first after the 

effective date of this AD, do the following: 

(1) Using the Flight Count Factor of 3, 

review and correct the critical part record for 

compressor rear hubs, P/N 3018111. Use 

paragraph 3 of the Accomplishment 

Instructions of PWC Service Bulletin (SB) No. 

PT6B–72–11002, Revision 8, dated June 11, 

2003, to do this. 

(2) Remove the compressor rear hub from 

service before further flight, if its life limit is 

found to be at or higher than the published 

life limit in PWC SB No. PT6B–72–11002, 

Revision 8, dated June 11, 2003. 

Alternative Methods of Compliance 

(g) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Special Flight Permits 

(h) Under 14 CFR part 39.23, we are 

limiting the special flight permits for this AD 

by allowing the engine to operate an 

additional 25 cycles-in-service or 25 

operating hours, whichever occurs first, for 

moving the helicopter to a location where the 

requirements of this AD can be done. 

Material Incorporated by Reference 

(i) You must use Pratt & Whitney Canada 

Service Bulletin No. PT6B–72–11002, 

Revision 8, dated June 11, 2003, to perform 

the reviews and corrections required by this 

AD. The Director of the Federal Register 

approved the incorporation by reference of 

this service bulletin in accordance with 5 

U.S.C. 552(a) and 1 CFR part 51. You can get 

a copy from Pratt & Whitney Canada, 1000 

Marie-Victorin, Longueuil, Quebec, Canada 

J4G1A1. You may review copies at the 

Docket Management Facility; U.S. 

Department of Transportation, 400 Seventh 

Street, SW., Nassif Building, Room PL–401, 

Washington, DC 20590–001, on the Internet 

at http://dms.dot.gov; or at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at NARA, call 202–741–6030, 

or go to: http://www.archives.gov/federal_

register/code_of_federal_regulations/

ibr_locations.html.

Related Information 

(j) Transport Canada airworthiness 

directive CF–2003–16, dated June 27, 2003, 

also addresses the subject of this AD.

Issued in Burlington, Massachusetts, on 

September 24, 2004. 

Francis A. Favara, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service.

[FR Doc. 04–21913 Filed 9–30–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NE–35–AD; Amendment 

39–13806; AD 2004–20–01] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada Models PW123, 

PW123B, PW123C, PW123D, PW123E, 

PW123AF, PW124B, PW125B, PW126A, 

PW127, PW127E, PW127F, and 

PW127G Turboprop Engines

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Pratt & 

Whitney Canada (PWC) models PW123, 

PW123B, PW123C, PW123D, PW123E, 

PW123AF, PW124B, PW125B, PW126A, 

PW127, PW127E, PW127F, and 

PW127G turboprop engines. This AD 

requires initial and repetitive gap 

inspections of the bypass valve cover, 

on certain part number (P/N) 

mechanical fuel controls (MFCs), and 

replacement of those MFCs as 

mandatory terminating action to the 

repetitive inspections. This AD is 

prompted by sixteen reports of loss of 

engine throttle response and overspeed, 

eight of which resulted in in-flight 

shutdown. We are issuing this AD to 

prevent loss of throttle response and 

overspeed, resulting in engine in-flight 

shutdown.

DATES: This AD becomes effective 

November 5, 2004. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of November 5, 2004.

ADDRESSES: You can get the service 

information identified in this AD from 

Honeywell Engines & Systems, 

Technical Publications Department, 111 

South 34th Street, Phoenix, Arizona 

85034; telephone (602) 365–5535; fax 

(602) 365–5577. 

You may examine the AD docket at 

the FAA, New England Region, Office of 

the Regional Counsel, 12 New England 

Executive Park, Burlington, MA. You 

may examine the service information, at