Federal Register / Vol. 69, No. 30 / Friday, February 13, 2004 / Rules and Regulations 7111

by the contractor), the borrower (acting 

through its architect or engineer, if 

applicable) will obtain executed copies 

of the following documents: 

(i) RUS Form 187, Certificate of 

Completion, Contract Construction. 

(ii) RUS Form 213, ‘‘Buy American’’

certificate. 

(iii) RUS Form 224, Waiver and 

Release of Lien, from each 

manufacturer, supplier, and contractor 

which has furnished material or services 

or both in connection with the 

construction. 

(iv) RUS Form 231, Certificate of 

Contractor. 

(v) RUS Form 254, Construction 

Inventory, including all supporting 

documents, such as RUS Forms 254a–c, 

construction change orders, and 

amendments for contracts executed on 

RUS Form 830. 

(vi) Certification by the project 

architect or engineer in accordance with 

§ 1726.403(a), if applicable. 

(vii) Final design documents, as 

outlined in part 1724 of this chapter. 

(2) Distribution of closeout 

documents. (i) The borrower will retain 

one copy of each of the documents 

identified in paragraph (c)(1) of this 

section in accordance with applicable 

RUS requirements regarding retention of 

records. 

(ii) For contracts subject to RUS 

approval, the borrower will submit the 

following closeout documents for RUS 

approval (through the GFR except for 

generation projects): 

(A) RUS Form 187, Certificate of 

Completion, Contract Construction. 

(B) RUS Form 231, Certificate of 

Contractor. 

(C) RUS Form 254, Construction 

Inventory, including all supporting 

documents, such as RUS Forms 254a–c 

and construction change orders, for 

contracts executed on RUS Form 830. 

(iii) For contracts not subject to RUS 

approval, the closeout is not subject to 

RUS approval. The borrower will send 

one copy of RUS Form 187 to RUS for 

information prior to or in conjunction 

with the applicable RUS Form 219, 

Inventory of Work Orders. The 

remaining closeout documents need not 

be sent to RUS unless specifically 

requested by RUS.

* * * * *

■ 23. Amend § 1726.404 by revising the 

introductory text to read as follows:

§ 1726.404 Non-site specific construction 

contract closeout. 

This section is applicable to contracts 

executed on RUS Form 790.

* * * * *

PART 1755—TELECOMMUNICATIONS 

STANDARDS AND SPECIFICATIONS 

FOR MATERIALS, EQUIPMENT, AND 

CONSTRUCTION

■ 24. The authority citation for part 1755 

continues to read as follows:

Authority: 7 U.S.C. 901 et seq., 1921 et 

seq., 6941 et seq.

■ 25. Amend § 1755.30 by revising 

paragraphs (c)(4) through (c)(8), (c)(12) 

through (c)(14), (c)(17), and (c)(24) to 

read as follows:

§ 1755.30 List of telecommunications 

standard contract forms.

* * * * *

(c) * * *

(4) RUS Form 168b, issued 2–04, 

Contractor’s Bond. 

(5) RUS Form 168c, issued 2–04, 

Contractor’s Bond. 

(6) RUS Form 181a, issued 3–66, 

Certificate of Completion (Force 

Account Construction). 

(7) RUS Form 187, issued 2–04, 

Certificate of Completion, Contract 

Construction. 

(8) RUS Form 213, issued 2–04, 

Certificate (Buy American).

* * * * *

(12) RUS Form 224, issued 2–04, 

Waiver and Release of Lien. 

(13) RUS Form 231, issued 2–04, 

Certificate of Contractor. 

(14) RUS Form 238, issued 2–04, 

Construction or Equipment Contract 

Amendment.

* * * * *

(17) RUS Form 257, issued 2–04, 

Contract to Construct Buildings.

* * * * *

(24) RUS Form 307, issued 2–04, Bid 

Bond.

* * * * *

Dated: January 30, 2004. 

Hilda Gay Legg, 

Administrator, Rural Utilities Service.

[FR Doc. 04–3115 Filed 2–12–04; 8:45 am] 

BILLING CODE 3410–15–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–11–AD; Amendment 

39–13459; AD 2004–03–15] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model DHC–8–102, –103, –106, –201, 

–202 –301, –311, and –315 Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to certain Bombardier Model 

DHC–8–102, –103, –106, –201, –202, 

–301, –311, and –315 airplanes, that 

currently requires a one-time inspection 

to detect chafing of electrical wires in 

the cable trough below the cabin floor; 

repair, if necessary; installation of 

additional tie-mounts and tie-wraps; 

and application of sealant to rivet heads. 

This amendment requires adding an 

additional modification of the electrical 

wires in certain sections. The actions 

specified by this AD are intended to 

prevent chafing of electrical wires, 

which could result in an uncommanded 

shutdown of an engine during flight. 

This action is intended to address the 

identified unsafe condition.

DATES: Effective March 19, 2004. 

The incorporation by reference of a 

certain publication, as listed in the 

regulations, is approved by the Director 

of the Federal Register as of March 19, 

2004. 

The incorporation by reference of a 

certain other publication, as listed in the 

regulations, was approved previously by 

the Director of the Federal Register as of 

October 27, 1998 (63 FR 50501), 

September 22, 1998).

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Bombardier, Inc., Bombardier 

Regional Aircraft Division, 123 Garratt 

Boulevard, Downsview, Ontario M3K 

1Y5, Canada. This information may be 

examined at the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, Rules Docket, 

1601 Lind Avenue, SW., Renton, 

Washington; or at the FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Westbury, New York; 

or at the Office of the Federal Register, 

800 North Capitol Street, NW., suite 

700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Douglas G. Wagner, Aerospace Engineer, 

Systems and Flight Test Branch, ANE–

172, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Westbury, New York, New 

York 11581; telephone (516) 228–7306; 

fax (516) 794–5531.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 99–21–09, 

amendment 39–11352 (64 FR 54199, 

October 6, 1999), which is applicable to 

certain Bombardier Model DHC–8–102, 

–103, –106, –201, –202, –301, –311, and 

–315 airplanes, was published in the 

Federal Register on October 20, 2003

7112 Federal Register / Vol. 69, No. 30 / Friday, February 13, 2004 / Rules and Regulations 

(68 FR 59892). The action proposed to 

continue to require a one-time 

inspection to detect chafing of electrical 

wires in the cable trough below the 

cabin floor; repair, if necessary; 

installation of additional tie-mounts and 

tie-wraps; and application of sealant to 

rivet heads. The action also proposed to 

add an additional modification of the 

electrical wires in certain sections. 

Comment 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

single comment received. 

The commenter notes that the 

proposed AD specifies accomplishment 

of the modification (including a general 

visual inspection and any applicable 

repair) per Part III, paragraphs 1 through 

9 and 12 through 20, of the 

Accomplishment Instructions of 

Bombardier Service Bulletin 8–53–80, 

Revision A, dated July 25, 2000. The 

commenter states that operators may 

have already accomplished the actions 

per the original issue of the service 

bulletin (Bombardier Service Bulletin 8–

53–80, dated December 22, 1999). The 

commenter adds that the only difference 

between the original issue and Revision 

A is that the number of work hours was 

not specified in the original issue. The 

commenter asks that the proposed AD 

be changed to give credit for using the 

original issue of the service bulletin. We 

agree with the commenter and have 

changed this final rule accordingly. 

Conclusion 

After careful review of the available 

data, including the comment noted 

above, we have determined that air 

safety and the public interest require the 

adoption of the rule with the change 

previously described. We have 

determined that this change will neither 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Cost Impact 

There are approximately 173 

airplanes of U.S. registry that will be 

affected by this AD. 

The actions that are currently 

required by AD 99–21–09 take between 

80 and 100 work hours per airplane 

(depending on the airplane model) to 

accomplish, at an average labor rate of 

$65 per work hour. Required parts are 

provided by the manufacturer at no cost 

to the operator. Based on these figures, 

the cost impact of the currently required 

actions is estimated to be between 

$5,200 and $6,500 per airplane. 

The additional modification that is 

required in this AD action will take 

about 10 work hours per airplane to 

accomplish, at an average labor rate of 

$65 per work hour. Required parts will 

be provided by the manufacturer at no 

cost to the operator. Based on these 

figures, the cost impact of the required 

modification on U.S. operators is 

estimated to be $112,450, or $650 per 

airplane.

The cost impact figures discussed 

above are based on assumptions that no 

operator has yet accomplished any of 

the requirements of this AD action, and 

that no operator would accomplish 

those actions in the future if this AD 

were not adopted. The cost impact 

figures discussed in AD rulemaking 

actions represent only the time 

necessary to perform the specific actions 

actually required by the AD. These 

figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

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 

removing amendment 39–11352 (64 FR 

54199, October 6, 1999), and by adding 

a new airworthiness directive (AD), 

amendment 39–13459, to read as 

follows:

2004–03–15 Bombardier, Inc. (Formerly de 

Havilland, Inc.): Amendment 39–13459. 

Docket 2002–NM–11–AD. Supersedes 

AD 99–21–09, Amendment 39–11352.

Applicability: Model DHC–8–102, –103, 

–106, –201, –202, –301, –311, and –315 

airplanes; serial numbers 3 through 540 

inclusive, excluding serial number 462; 

certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent chafing of electrical wires, 

which could result in an uncommanded 

shutdown of an engine during flight, 

accomplish the following: 

Restatement of Requirements of AD 99–21–

09 

One-Time Inspection, Corrective Action, and 

Modification 

(a) Perform a one-time general visual 

inspection to detect chafing of electrical 

wires in the cable trough below the cabin 

floor; install additional tie-mounts and tiewraps; and apply sealant to rivet heads 

(reference Bombardier Modification 8/2705); 

in accordance with Bombardier Service 

Bulletin S.B. 8–53–66, dated March 27, 1998, 

at the time specified in paragraph (a)(1) or 

(a)(2) of this AD, as applicable. If any chafing 

is detected during the inspection required by 

this paragraph, prior to further flight, repair 

in accordance with the service bulletin.

Note 1: For the purposes of this AD, a 

general visual inspection is defined as: ‘‘A 

visual examination of an interior or exterior 

area, installation, or assembly to detect 

obvious damage, failure, or irregularity. This 

level of inspection is made from within 

touching distance unless otherwise specified. 

A mirror may be necessary to enhance visual 

access to all exposed surfaces in the 

inspection area. This level of inspection is 

made under normally available lighting 

conditions such as daylight, hangar lighting, 

flashlight, or droplight and may require 

removal or opening of access panels or doors. 

Stands, ladders, or platforms may be required 

to gain proximity to the area being checked.’’

(1) For airplanes having serial numbers 3 

through 519 inclusive, excluding serial 

number 462: Inspect within 36 months after 

October 27, 1998 (the effective date of AD 

98–20–14, amendment 39–10781). 

(2) For airplanes having serial numbers 520 

through 540 inclusive: Inspect within 36 

months after November 10, 1999 (the 

effective date of AD 99–21–09, amendment 

39–11352, which superseded AD 98–20–14),

Federal Register / Vol. 69, No. 30 / Friday, February 13, 2004 / Rules and Regulations 7113

or at the next ‘‘C’’ check, whichever occurs 

first. 

New Requirements of This AD 

Modification 

(b) For all airplanes: Within 36 months 

after the effective date of this AD; modify the 

electrical wires in the cable trough below the 

cabin floor at Sections X510.00 to X580.50 

(including a general visual inspection and 

any applicable repair) per Part III, paragraphs 

1 through 9 and 12 through 20, of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–53–80, Revision ‘A’, dated 

July 25, 2000. Any applicable repair must be 

done before further flight. Accomplishment 

of these actions before the effective date of 

this AD per Bombardier Service Bulletin 8–

53–80, dated December 22, 1999, is 

considered acceptable for compliance with 

the actions required by this paragraph. 

Alternative Methods of Compliance 

(c) In accordance with 14 CFR 39.19, the 

Manager, New York Aircraft Certification 

Office, FAA is authorized to approve 

alternative methods of compliance for this 

AD. 

Incorporation by Reference 

(d) The actions shall be done in accordance 

with Bombardier Service Bulletin S.B. 8–53–

66, dated March 27, 1998; and Bombardier 

Service Bulletin 8–53–80, Revision ‘A’, dated 

July 25, 2000; as applicable. 

(1) The incorporation by reference of 

Bombardier Service Bulletin 8–53–80, 

Revision ‘A’, dated July 25, 2000; is approved 

by the Director of the Federal Register in 

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

part 51. 

(2) The incorporation by reference of 

Bombardier Service Bulletin S.B. 8–53–66, 

dated March 27, 1998; was approved 

previously by the Director of the Federal 

Register as of October 27, 1998 (63 FR 50501, 

September 22, 1998). 

(3) Copies may be obtained from 

Bombardier, Inc., Bombardier Regional 

Aircraft Division, 123 Garratt Boulevard, 

Downsview, Ontario M3K 1Y5, Canada. 

Copies may be inspected at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or at the 

FAA, New York Aircraft Certification Office, 

1600 Stewart Avenue, Westbury, New York; 

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 Canadian airworthiness directive CF–

1998–08R2, dated July 10, 2000.

Effective Date 

(e) This amendment becomes effective on 

March 19, 2004.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2576 Filed 2–12–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–SW–45–AD; Amendment 

39–13471; AD 2004–03–27] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model AS332C, L, and L1 

Helicopters

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

specified Eurocopter France 

(Eurocopter) model helicopters that 

requires inspecting the bevel gear for a 

crack using a borescope. This 

amendment is prompted by a crack that 

was detected on a bevel gear during a 

main gearbox teardown inspection. The 

actions specified by this AD are 

intended to prevent failure of the bevel 

gear, loss of torque to the main rotor 

system, and subsequent loss of control 

of the helicopter.

DATES: Effective March 19, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of March 19, 

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:

Uday Garadi, Aviation Safety Engineer, 

FAA, Rotorcraft Directorate, Safety 

Management Group, Fort Worth, Texas 

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

fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an AD that is applicable to 

Eurocopter Model AS332C, L, and L1 

helicopters was published in the 

Federal Register on December 31, 2002 

(67 FR 79893). That action proposed to 

require inspecting the bevel gear for 

cracks using a borescope within 50 

hours TIS, and thereafter at intervals not 

to exceed 150 hours TIS, for bevel gears 

with more than 6,600 hours TIS. If a 

crack was found in the bevel gear, it was 

proposed that replacing the bevel gear 

would be required. However, before the 

final rule was published, we discovered 

that certain part-numbered bevel gears 

were omitted from the applicability and 

one was incorrectly stated in that 

previous proposal. Also, the 

manufacturer revised the service 

information to introduce the new 

inspection interval of 1,000 cycles for 

helicopter operations involving a torque 

application frequency of more than 4 

cycles per hour for helicopters that 

conduct external load operations 

involving more frequent torque 

applications. Additionally, we 

inadvertently included Model AS332C1 

helicopters in the ‘‘Applicability’’

section of the proposal—those model 

helicopters are not on the U.S. Registry. 

Finally, the DGAC issued a revised AD 

for helicopters operated in France. 

Therefore, we reopened the comment 

period by publishing a supplemental 

notice of proposed rulemaking on 

September 18, 2003 (68 FR 54686). That 

action: 

• Corrected the basic bevel gear part 

number (P/N) stated in the 

‘‘Applicability’’ of the proposal to state 

‘‘332A32–2181–00’’; 

• Added bevel gear P/Ns 332A32–

2181–01 and –08 to the ‘‘Applicability’’; 

• Deleted the Model AS332C1 

helicopters from the ‘‘Applicability’’; 

• Incorporated the latest Eurocopter 

Alert Telex and referenced the latest 

DGAC AD; 

• Proposed requiring the repetitive 

inspection at intervals not to exceed 150 

hours TIS or 1,000 torque cycles, 

whichever occurs first; and 

• Excluded from the ‘‘Applicability’’

any main gearbox (regardless of the P/

N of the main reduction gear module or 

bevel gear) overhauled after December 

31, 2002, and any P/N inspected in 

accordance with AS332 letter to Repair 

Stations No. 183 or repaired in 

accordance with Repair Sheet (F.R.) 

332A32–2181–ZA or 331A32–3110–ZA.

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 AS332C, C1, L, and 

L1 helicopters. The DGAC advises that 

borescope inspections of the bevel gear 

are necessary to detect cracks. 

Eurocopter has issued Alert Telex No. 

05.00.58 R2, dated February 3, 2003, 

which indicates that as a result of metal 

particles found on the chip detector of 

the main gearbox sump on a helicopter, 

further investigation has revealed a 

longitudinal crack that grows 

lengthwise in the shaft, up to the