Federal Register / Vol. 69, No. 6 / Friday, January 9, 2004 / Rules and Regulations 1519

TABLE 1.—ACCEPTABLE SERVICE BULLETIN REVISIONS

Operators that have— May take credit for compliance 

with— 

If that action was done before the effective date of this AD in 

accordance with EMBRAER Service Bulletin— 

Inspected the pitot-TAT relays and done applicable corrective actions.Paragraph (a) of this AD ......... 145–30–0032, Change 02, dated December 3, 2001; or 

Change 03, dated January 27, 2003. 

Modified the seal ................................................ Paragraph (c) of this AD ......... 145–30–0032, Change 02, dated December 3, 2001; or 

Change 03, dated January 27, 2003. 

Installed protective sheets ................................. Paragraph (d) of this AD ......... 145–25–0211, dated April 27, 2001; Part I. 

145–25–0211, Change 01, dated May 25, 2001; Part I. 

145–25–0211, Change 02, dated June 17, 2001; Part I. 

145–25–0211, Change 03, dated December 3, 2001; Part I. 

145–25–0211, Change 04, dated February 6, 2002; Part I. 

145–25–0211, Change 05, dated April 16, 2002; Part I. 

145–25–0211, Change 06, dated December 26, 2002; Part I. 

145–25–0211, Change 07, dated August 11, 2003; Part I. 

145–30–0032, Change 02, dated December 3, 2001; Part III. 

145–30–0032, Change 03, dated January 27, 2003; Part III. 

Alternative Methods of Compliance 

(f) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, 

FAA, Transport Airplane Directorate, is 

authorized to approve alternative methods of 

compliance for this AD. 

Incorporation by Reference 

(g) Unless otherwise specified in this AD, 

the actions must be done in accordance with 

EMBRAER Service Bulletin 145–30–0032, 

Change 04, dated August 11, 2003; and 

EMBRAER Service Bulletin 145–76–0003, 

dated April 22, 2002; as applicable. 

EMBRAER Service Bulletin 145–30–0032, 

Change 04, contains the following effective 

pages:

Page No. Change level shown on page Date shown on page 

1, 2, 7, 8, 21, 22 ................................................................... 04 ......................................................................................... August 11, 2003. 

3–6, 9–20 ............................................................................. 02 ......................................................................................... December 3, 2001. 

This incorporation by reference was 

approved by the Director of the Federal 

Register in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. Copies may be obtained 

from Empresa Brasileira de Aeronautica S.A. 

(EMBRAER), P.O. Box 343—CEP 12.225, Sao 

Jose dos Campos—SP, Brazil. Copies may be 

inspected at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or at the Office of the Federal 

Register, 800 North Capitol Street, NW., suite 

700, Washington, DC.

Note 2: The subject of this AD is addressed 

in Brazilian airworthiness directives 2001–

05–01R2, dated April 22, 2003; and 2002–10–

03, dated October 24, 2002.

Effective Date 

(h) This amendment becomes effective on 

February 13, 2004.

Issued in Renton, Washington, on 

December 31, 2003. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–269 Filed 1–8–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–SW–24–AD; Amendment 

39–13423; AD 2004–01–09] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model AS355E, F, F1, F2, and 

N Helicopters

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

specified Eurocopter France (ECF) 

model helicopters that requires revising 

the Limitations section of the Rotorcraft 

Flight Manual (RFM) to prohibit using 

the landing light except for landing and 

takeoff until the 40 amp 10P1 and 10P2 

contactors are replaced with 50 amp 

circuit breakers. Also, this amendment 

requires upgrading the electrical master 

boxes. This amendment is prompted by 

three reports of complete loss of 

electrical power generating systems, 

except for the direct battery power, due 

to a combination of high outside 

temperature and long flight duration 

with the landing light on that causes the 

nontemperature compensated trip 

switches to prematurely trip. The 

actions specified by this AD are 

intended to prevent failure of the 

helicopter power generator systems, loss 

of the use of flight instruments, and 

subsequent loss of control of the 

helicopter.

DATES: Effective February 13, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of February 

13, 2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from American Eurocopter Corporation, 

2701 Forum Drive, Grand Prairie, Texas 

75053–4005, telephone (972) 641–3460, 

fax (972) 641–3527. This information 

may be examined at the FAA, Office of 

the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 

663, Fort Worth, Texas; or at the Office 

of the Federal Register, 800 North 

Capitol Street, NW., suite 700, 

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Carroll Wright, Aviation Safety 

Engineer, FAA, Rotorcraft Directorate, 

Regulations and Guidance Group, Fort 

Worth, Texas 76193–0111, telephone 

(817) 222–5120, fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: A 

proposal to amend 14 CFR part 39 to 

include an AD for the specified ECF 

1520 Federal Register / Vol. 69, No. 6 / Friday, January 9, 2004 / Rules and Regulations 

model helicopters was published in the 

Federal Register on September 18, 2003 

(68 FR 54688). That action proposed to 

require temporarily revising the 

Limitations section of the RFM to 

prohibit use of the landing light except 

for landing and takeoff by making pen 

and ink changes or adding a copy of the 

AD to the RFM. Also proposed was, 

within 6 months, or before the next 

instrument flight rule (IFR) flight, 

whichever occurs first, replacing 

nontemperature compensated 40-amp 

contactors 10P1 and 10P2 with 

temperature compensated 50-amp 

circuit breakers. 

The Direction Generale De L’Aviation 

Civile (DGAC), the airworthiness 

authority for France, notified the FAA 

that an unsafe condition may exist on 

the specified ECF model helicopters. 

The DGAC advises of three reports of 

complete electrical power failure, 

except direct battery power, that 

occurred during flights with high 

outside air temperature (above 25 

degrees Celsius) and use of the landing 

light for more than 1 hour. The failures 

were due to the disengagement of 40-

ampere (amp) contactors (trip switches 

MP 1648) in the electrical power 

systems below their nominal threshold. 

These trip switches are not temperature 

compensated and accordingly may trip 

based on the internal temperature of the 

electrical master boxes. 

Eurocopter has issued Service Telex 

No. 25.00.63, dated August 2, 2000 

(Telex), specifying to not use the 

landing light outside the landing and 

takeoff phases and Alert Service 

Bulletin AS 355, No. 24.00.14, dated 

November 28, 2002, specifying an 

upgrade of the electrical master boxes 

on or before August 1, 2003. The DGAC 

classified these service bulletins as 

mandatory and issued AD Nos. 2000–

339–060(A), dated August 23, 2000; 

2000–339–060(A) R1, dated September 

6, 2000; and 2000–339–060(A) R2, dated 

December 24, 2002, to ensure the 

continued airworthiness of these 

helicopters in France. 

These helicopter models are 

manufactured in France and are type 

certificated for operation in the United 

States under the provisions of 14 CFR 

21.29 and the applicable bilateral 

airworthiness agreement. Pursuant to 

this bilateral airworthiness agreement, 

the DGAC has kept the FAA informed 

of the situation described above. The 

FAA has examined the findings of the 

DGAC, reviewed all available 

information, and determined that AD 

action is necessary for products of these 

type designs that are certificated for 

operation in the United States. 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were received on the 

proposal or the FAA’s determination of 

the cost to the public. The FAA has 

determined that air safety and the 

public interest require the adoption of 

the rule as proposed. 

The FAA estimates that this AD will: 

• Affect 442 helicopters of U.S. 

registry, 

• Take 1⁄2 work hour per helicopter to 

add information to the Limitations 

section of the RFM, and 

• Take 4 hours to upgrade the 

electrical boxes. 

The average labor rate is $65 per work 

hour. The required parts will cost 

approximately $1707. Based on these 

figures, the total cost impact of the AD 

on U.S. operators is estimated to be 

$883,779. 

The regulations adopted herein 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. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (1) is not a 

‘‘significant regulatory action’’ under 

Executive Order 12866; (2) is not a 

‘‘significant rule’’ under 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. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

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. Section 39.13 is amended by adding 

a new airworthiness directive to read as 

follows:

2004–01–09 Eurocopter France:

Amendment 39–13423. Docket No. 

2003–SW–24–AD.

Applicability: Model AS355E, F, F1, F2, 

and N helicopters, certificated in any 

category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent failure of the electrical power 

generating systems, loss of the use of flight 

instruments, and subsequent loss of control 

of the helicopter, accomplish the following: 

(a) Before further flight and until you 

replace the circuit breakers in accordance 

with paragraph (b) of this AD, revise the 

Limitations section of the Rotorcraft Flight 

Manual (RFM) to prohibit use of the landing 

light except for the landing and takeoff 

phases of flight by making pen and ink 

changes, or inserting a copy of this AD into 

the Limitations section of the RFM.

Note 1: Eurocopter France Service Telex 

25.00.63, dated August 2, 2000, pertains to 

the subject of this AD.

(b) Within 6 months or before the next 

instrument flight rule (IFR) operation, 

whichever occurs first, upgrade the electrical 

master boxes and replace the nontemperature 

compensated 40-amp contactors (circuit 

breakers) 10P1 and 10P2 with temperature 

compensated 50-amp circuit breakers, part 

number P/N 84–306–050 (B) or 5TC50–50 

(C), in accordance with the Accomplishment 

Instructions, paragraph 2.B, of Eurocopter 

Alert Service Bulletin AS355, No. 24.00.14, 

dated November 28, 2002. 

(c) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Safety 

Management Group, Rotorcraft Directorate, 

FAA, for information about previously 

approved alternative methods of compliance. 

(d) Modifying the electrical master boxes 

and replacing the nontemperature 

compensated 40-amp contractors (circuit 

breakers) must be done in accordance with 

Eurocopter Alert Service Bulletin AS 355, 

No. 24.00.14, dated November 28, 2002. The 

Director of the Federal Register approved this 

incorporation by reference in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Copies may be obtained from American 

Eurocopter Corporation, 2701 Forum Drive, 

Grand Prairie, Texas 75053–4005, telephone 

(972) 641–3460, fax (972) 641–3527. Copies 

may be inspected at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas; or at the Office of the Federal Register, 

800 North Capitol Street, NW., suite 700, 

Washington, DC. 

(e) This amendment becomes effective on 

February 13, 2004.

Note 2: The subject of this AD is addressed 

in Direction Generale De L’Aviation Civile 

(France) ADs 2000–339–060(A) dated August 

23, 2000; 2000–339–060(A) R1, dated 

September 6, 2000; and 2000–339–060(A) R2, 

dated December 24, 2002.

Federal Register / Vol. 69, No. 6 / Friday, January 9, 2004 / Rules and Regulations 1521

Issued in Fort Worth, Texas, on December 

23, 2003. 

Kim Smith, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service.

[FR Doc. 04–268 Filed 1–8–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–SW–41–AD; Amendment 

39–13428; AD 2004–01–14] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model EC130B4 Helicopters

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for 

Eurocopter France (Eurocopter) Model 

EC130B4 helicopters with a certain air 

intake cowling attachment fitting 

(fitting) installed. This action requires 

inspecting for broken or cracked 

forward fittings. If a broken or cracked 

fitting is found, inspecting the four 

center and aft fittings for cracks is 

required. Replacing broken fittings or 

certain cracked fittings is also required. 

This amendment is prompted by reports 

of cracked and broken fittings; one 

fitting failed after only 418 hours timein-service (TIS). This condition, if not 

corrected, could result in failure of a 

forward fitting, an excess load on the 

other fittings, which could cause them 

to crack and break, which could result 

in loss of the air intake cowling in flight, 

and subsequent damage or loss of 

control of the helicopter, or both.

DATES: Effective January 26, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of January 26, 

2004. 

Comments for inclusion in the Rules 

Docket must be received on or before 

March 8, 2004.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Office of the 

Regional Counsel, Southwest Region, 

Attention: Rules Docket No. 2003–SW–

41–AD, 2601 Meacham Blvd., Room 

663, Fort Worth, Texas 76137. You may 

also send comments electronically to 

the Rules Docket at the following 

address: 9-asw-adcomments@faa.gov.

The service information referenced in 

this AD may be obtained from American 

Eurocopter Corporation, 2701 Forum 

Drive, Grand Prairie, Texas 75053–4005, 

telephone (972) 641–3460, fax (972) 

641–3527. This information may be 

examined at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas; or at the Office of the 

Federal Register, 800 North Capitol 

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Ed 

Cuevas, Aviation Safety Engineer, FAA, 

Rotorcraft Directorate, Safety 

Management Group, Fort Worth, Texas 

76193–0111, telephone (817) 222–5355, 

fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: The 

Direction Generale De L’Aviation Civile 

(DGAC), the airworthiness authority for 

France, notified the FAA that an unsafe 

condition may exist on Eurocopter 

Model EC130B4 helicopters with 

fittings, part number (P/N) 350A25–

0405–00, –01, –02, –03, –04, and –05, 

installed. The DGAC advises that there 

have been cases of cracks and failures of 

fittings. 

Eurocopter France has issued 

Eurocopter Alert Service Bulletin No. 

53A004, dated September 11, 2003, 

which specifies inspecting the fittings 

for cracks and replacing failed fittings or 

those with more than 2 cracks or 1 crack 

that exceeds 10 mm in length. The alert 

service bulletin permits operators to 

stop-drill up to two cracks provided that 

no crack exceeds 10 mm in length and 

that the fitting is inspected every 20 

flying hours, at the lastest. The DGAC 

classified this alert service bulletin as 

mandatory and issued AD 2003–358(A), 

dated October 15, 2003, to ensure the 

continued airworthiness of these 

helicopters in France. 

This helicopter model is 

manufactured in France and is type 

certificated for operation in the United 

States under the provisions of 14 CFR 

21.29 and the applicable bilateral 

agreement. Pursuant to the applicable 

bilateral agreement, the DGAC has kept 

the FAA informed of the situation 

described above. The FAA has 

examined the findings of the DGAC, 

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. 

This unsafe condition is likely to exist 

or develop on other helicopters of the 

same type design registered in the 

United States. Therefore, this AD is 

being issued to prevent failure of a 

forward fitting, an excess load on the 

other fittings, which could cause them 

to crack and break, which could result 

in loss of the air intake cowling in flight, 

and subsequent damage or loss of 

control of the helicopter, or both. This 

AD requires: 

• For helicopters with less than 100 

hours TIS, inspecting the forward 

fittings no later than 110 hours TIS, then 

at intervals not to exceed 110 hours TIS; 

• For helicopters with 100 or more 

hours TIS, inspecting the forward 

fittings within the next 10 hours TIS, 

then at intervals not to exceed 110 hours 

TIS; 

• If one or two forward fittings are 

broken or cracked, inspecting the center 

and aft fittings for breaks or cracks 

before further flight; 

• If any fitting is broken, has a crack 

that exceeds 10 mm in length, or has 

more than 2 cracks, replacing the fitting 

with an airworthy fitting before further 

flight; and 

• For helicopters with one or more 

cracked fitting with no more than two 

cracks on each fitting, and each crack 

length is less than or equal to 10mm, 

stop-drilling the cracks and inspecting 

the fitting at intervals not to exceed 20 

hours TIS. 

The actions must be done in 

accordance with the alert service 

bulletin described previously. The 

unsafe condition must be corrected in a 

very short time period because loss of 

an air intake cowling in flight can 

adversely affect the controllability or 

structural integrity of the helicopter. 

Therefore, the previously described 

actions are required, and this AD must 

be issued immediately. This AD is an 

interim action; Eurocopter is 

investigating to determine the cause of 

the cracked and failed fittings. Upon 

completion of that investigation, we 

may issue another AD with terminating 

action for the requirements of this AD. 

Since a situation exists that requires 

the immediate adoption of this 

regulation, it is found that notice and 

opportunity for prior public comment 

hereon are impracticable, and that good 

cause exists for making this amendment 

effective in less than 30 days.

The FAA estimates that this AD will 

affect 28 helicopters and will take 

approximately 1 work hour to inspect 

the two forward fittings. If cracked or 

broken fittings are found, an additional 

2 work hours will be required to inspect 

the center and aft fittings, and an 

additional 0.5 work hour will be 

required to replace each cracked or 

broken fitting. We estimate that the 

average labor rate will be $65 per work 

hour. We estimate that forward fittings 

cost $240 each and center and aft 

fittings cost $225 each. The estimated 

total cost of the AD for each year will