42956 Federal Register / Vol. 68, No. 139 / Monday, July 21, 2003 / Rules and Regulations 

Actions Compliance Procedures 

(1) Inspect the rudder control lever shafts, part 

numbers (P/N) 2/N–45–1102, 1/N–45–1103, 

and 1/N–45–1104 (or FAA-approved equivalent part numbers) for cracks. Use dye penetrant while the shaft is installed; or either dye 

penetrant inspection or magnetic particle 

methods if the shaft is removed.

Within the next 100 hours time-in-service 

(TIS) after September 8, 2003 (the effective 

date of this AD), unless already accomplished.

In accordance with Nomad Alert Service Bulletin ANMD–27–51, dated September 13, 

2002, and the applicable maintenance manual. 

(2) Inspect all lever shaft side plates on P/Ns 2/

N–45–1102, 1/N–45–1103, and 1/N–45–1104 

(or FAA-approved equivalent part numbers) 

by measuring the thickness for discrepancies.

Within the next 100 hours TIS after September 8, 2003 (the effective date of this 

AD), unless already accomplished.

In accordance with Nomad Alert Service Bulletin ANMD–27–51, dated September 13, 

2002, and the applicable maintenance manual. 

(3) Visually inspect all rudder control lever 

shafts P/Ns 2/N–45–1102, 1/N–45–1103, and 

1/N–45–1104 (or FAA-approved equivalent 

part numbers) for cracks.

Repetitively inspect at intervals not to exceed 

100 hours TIS after the inspection required 

in paragraph (d)(1) of this AD.

In accordance with Nomad Alert Service Bulletin ANMD–27–51, dated September 13, 

2002, and the applicable maintenance manual. 

(4) If damage is found during any inspection required by this AD.

(i) For lever shafts found with crack damage, 

replace with new or serviceable items 

Prior to further flight after any inspection required by this AD.In accordance with Nomad Alert Service Bulletin ANMD–27–51, dated September 13, 

2002, and the applicable maintenance manual. 

(ii) For discrepancies in the thickness of lever 

shaft side plates, obtain a repair scheme 

from the manufacturer through FAA at the 

address specified in paragraph (e) of this AD 

and incorporate this repair scheme 

(iii) Repairable and nonrepairable damage is 

defined in the service information 

(e) Can I comply with this AD in any other 

way?

(1) To use an alternative method of 

compliance or adjust the compliance time, 

follow the procedures in 14 CFR 39.13. Send 

these requests to the Manager, Los Angeles 

Aircraft Certification Office. For information 

on any already approved alternative methods 

of compliance, contact Ron Atmur, 

Aerospace Engineer, FAA, Los Angeles 

Aircraft Certification Office, 3960 Paramount 

Boulevard, Lakewood, California 90712; 

telephone (562) 627–5224; facsimile (562) 

627–5210. 

(2) Alternative methods of compliance 

approved in accordance with AD 82–12–06, 

which is superseded by this AD, are not 

approved as alternative methods of 

compliance with this AD. 

(f) Are any service bulletins incorporated 

into this AD by reference? Actions required 

by this AD must be done in accordance with 

Nomad Alert Service Bulletin ANMD–27–51, 

dated September 13, 2002. The Director of 

the Federal Register approved this 

incorporation by reference under 5 U.S.C. 

552(a) and 1 CFR part 51. You may get copies 

from Nomad Operations, Aerospace Support 

Division, Boeing Australia, PO Box 767, 

Brisbane, QLD 4000 Australia; telephone 61 

7 3306 3366; facsimile 61 7 3306 3111. You 

may view copies at the FAA, Central Region, 

Office of the Regional Counsel, 901 Locust, 

Room 506, Kansas City, Missouri, or at the 

Office of the Federal Register, 800 North 

Capitol Street, NW., suite 700, Washington, 

DC. 

(g) Does this AD action affect any existing 

AD actions? This amendment supersedes AD 

82–12–06, Amendment 39–4399.

Note: The subject of this AD is addressed 

in Australian AD GAF–N22/44, dated 

November 14, 2002.

(h) When does this amendment become 

effective? This amendment becomes effective 

on September 8, 2003.

Issued in Kansas City, Missouri, on July 10, 

2003. 

Dorenda D. Baker, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 03–17945 Filed 7–18–03; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–165–AD; Amendment 

39–13225; AD 2003–14–06] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–200, –200C, –300, –400, and 

–500 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This document corrects a 

typographical error that appeared in 

airworthiness directive (AD) 2003–14–

06 that was published in the Federal 

Register on July 9, 2003 (68 FR 40759). 

The typographical error resulted in an 

incorrect AD number in one location of 

the document. This AD is applicable to 

certain Boeing Model 737–200, –200C, 

–300, –400, and –500 series airplanes. 

This AD requires repetitive inspections 

for cracking of certain lap splices, and 

corrective action if necessary.

DATES: Effective July 14, 2003.

FOR FURTHER INFORMATION CONTACT:

Duong Tran, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6452; fax (425) 917–6590.

SUPPLEMENTARY INFORMATION:

Airworthiness Directive (AD) 2003–14–

06, amendment 39–13225, applicable to 

certain Boeing Model 737–200, –200C, 

–300, –400, and –500 series airplanes, 

was published in the Federal Register

on July 9, 2003 (68 FR 40759). That AD 

requires repetitive inspections for 

cracking of certain lap splices, and 

corrective action if necessary. 

As published, the AD number appears 

as ‘‘2003–14–60’’ in the Product 

Identification line in the regulatory text 

of the AD. The correct AD number is 

2003–14–06. The number is referenced 

correctly throughout the remainder of 

the document. 

Since no other part of the regulatory 

information has been changed, the final 

rule is not being republished in the 

Federal Register. 

The effective date of this AD remains 

July 14, 2003.

§ 39.13 [Corrected]

■ On page 40761, in the first column, the 

Product Identification line of AD 2003–

14–06 is corrected to read as follows:

* * * * *

Federal Register / Vol. 68, No. 139 / Monday, July 21, 2003 / Rules and Regulations 42957

2003–14–06 Boeing: Amendment 39–13225. 

Docket 2003–NM–165–AD.

* * * * *

Issued in Renton, Washington, on July 15, 

2003. 

Ali Bahrami, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 03–18421 Filed 7–18–03; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–SW–56–AD; Amendment 

39–13231; AD 2003–14–12] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model SA330F, G, and J; 

AS332C, L, and L1; SA341G; SA342J; 

AS350B, BA, B1, B2, B3, and D; 

AS355E, F, F1, F2 and N; SA–365C, C1, 

and C2; SA–365N and N1; and AS–

365N2 and N3 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 

determining whether specified main or 

tail rotor (rotor) parts are installed and, 

if so, updating and recording the correct 

hours time-in-service (TIS) or cycles of 

each part. If the hours TIS or cycles of 

any rotor part exceed its life limit, this 

AD also requires replacing that part 

with an airworthy part within 50 hours 

TIS. This amendment is prompted by 

the need to correct the Equipment Log 

Card (FME) to accurately reflect the total 

hours TIS and cycles of certain repaired 

or overhauled rotor parts. The actions 

specified by this AD are intended to 

prevent failure of a life limited rotor 

part, loss of a rotor, and subsequent loss 

of control of the helicopter.

DATES: Effective August 25, 2003. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of August 25, 

2003.

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:

Uday Garadi, Aviation Safety Engineer, 

FAA, Rotorcraft Directorate, Rotorcraft 

Standards Staff, Fort Worth, Texas 

76193–0110, telephone (817) 222–5123, 

fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: A 

proposal to amend 14 CFR part 39 to 

include an AD for the specified model 

helicopters was published in the 

Federal Register on March 14, 2003 (68 

FR 12318). That action proposed to 

require determining whether specified 

rotor parts are installed and, if so, 

updating and recording the correct 

hours TIS or cycles of each part. If the 

hours TIS or cycles of any rotor part 

exceed its life limit, this AD would also 

require replacing that part with an 

airworthy part within 50 hours TIS. 

The Direction Generale De L’Aviation 

Civile (DGAC), the airworthiness 

authority for France, notified the FAA 

that an unsafe condition may exist on 

ECF Model SA330F, G, and J; AS332C, 

L, and L1; SA341G; SA342J; AS350B, 

BA, B1, B2, B3, and D; AS355E, F, F1, 

F2 and N; SA–365C, C1, and C2; SA–

365N and N1; and AS–365 N2 and N3 

helicopters. The DGAC advises of the 

discovery of a discrepancy in the 

computer program used to carry over 

the number of operating hours of parts 

following repair or overhaul, which is 

the cause of incorrect completion of 

FMEs. 

ECF has issued the following Alert 

Telexes for the helicopter model series 

specified: Nos. 65.110 for SA330, 

62.00.58 for AS332, 65.60 for SA341 

and SA342, 62.00.25 for AS350, 

62.00.27 for AS355, 65.41 for SA–365C, 

and 62.00.19 for AS–365N, all dated 

August 13, 2002. These alert telexes 

specify correcting the FME to list the 

correct total number of operating hours 

and cycles for specified parts installed 

on dynamic components. After 

correcting the FME, if the parts have 

exceeded their life limit, the alert 

telexes specify removing or monitoring 

the parts. The DGAC classified these 

alert telexes as mandatory and issued 

AD No. 2002–452(A), dated September 

4, 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 

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 these type designs 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 designs registered in the 

United States. Therefore, the AD 

requires, within 10 hours TIS, 

determining whether the specified rotor 

part and serial numbers are installed by 

reference to the FME and, if installed, 

correcting the hours TIS and cycles. If 

a part exceeds its life limit, the AD 

requires replacing the part within 50 

hours TIS. The actions would be 

required for the parts listed in the 

appendix of the alert telexes described 

previously. 

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. 

On July 10, 2002, the FAA issued a 

new version of 14 CFR part 39 (67 FR 

47997, July 22, 2002), which governs the 

FAA’s AD system. The regulation now 

includes material that relates to altered 

products, special flight permits, and 

alternative methods of compliance. 

However, for clarity and consistency in 

this final rule, we have retained the 

language of the NPRM regarding that 

material. 

The FAA estimates that this AD will 

affect 760 helicopters of U.S. registry, 

and the required actions will take 

approximately 1 work hour to determine 

the part and serial number and 8 hours 

to replace each affected part on 38 

helicopters (5 percent of the total 

affected helicopters). The average labor 

rate is $60 per work hour. Required 

parts will cost approximately $64,560 

depending on which part will be 

replaced. Based on these figures, we 

estimate the total cost impact of the AD 

on U.S. operators will be $2,517,120. 

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.