64832 Federal Register / Vol. 69, No. 216 / Tuesday, November 9, 2004 / Rules and Regulations 

application form and include the 

information contained in paragraphs 

(b)(3), (5), (7), (8), and (11) of this 

section. The lender must have the 

documentation identified in paragraph 

(b) of this section, with the exception of 

paragraphs (b)(1), (2), (14), and (15), 

available in its file for review.

Dated: November 2, 2004. 

Gilbert Gonzalez, 

Acting Under Secretary, Rural Development.

[FR Doc. 04–24886 Filed 11–8–04; 8:45 am] 

BILLING CODE 3410–XY–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–18579; Directorate 

Identifier 2004–CE–19–AD; Amendment 39–

13856; AD 2004–23–01] 

RIN 2120–AA64

Airworthiness Directives; Pilatus 

Aircraft Ltd. Model PC–7 Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for certain 

Pilatus Aircraft Ltd. (Pilatus) Model PC–

7 airplanes with any Lear Romec 

RR53710B type or Lear Romec 

RR53710K fuel booster pump (Pilatus 

part number 968.84.11.401; 

968.84.11.403; or 968.84.11.404) 

installed. This AD requires you to check 

the airplane logbook to determine 

whether any installed fuel booster pump 

has been modified with spiral wrap to 

protect the wire leads and has the suffix 

letter ‘‘B’’ added to the serial number of 

the fuel booster pump identification 

plate. If any installed fuel booster pump 

has not been modified, you are required 

to inspect any installed fuel booster 

pump wire lead for defects; if defects 

are found, replace the fuel booster pump 

with a modified fuel booster pump with 

spiral wrap that protects the wire leads; 

or if no defects are found, install spiral 

wrap to protect any wire leads and add 

the suffix letter ‘‘B’’ to the serial number 

of the fuel booster pump identification 

plate. The pilot is allowed to do the 

logbook check. If the pilot can positively 

determine that the fuel booster pump 

wire leads with spiral wrap are installed 

following the service information and 

that the suffix letter ‘‘B’’ is included in 

the serial number of the fuel booster 

pump identification plate, no further 

action is required. This AD is the result 

of mandatory continuing airworthiness 

information (MCAI) issued by the 

airworthiness authority for Switzerland. 

We are issuing this AD to detect and 

correct any defects in the leads of any 

fuel booster pump, which could result 

in electrical arcing. This failure could 

lead to a fire or explosion in the fuel 

tank.

DATES: This AD becomes effective on 

December 27, 2004. 

As of December 27, 2004, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation.

ADDRESSES: To get the service 

information identified in this AD, 

contact Pilatus Aircraft Ltd., Customer 

Liaison Manager, CH–6371 Stans, 

Switzerland; telephone: +41 41 619 

6208; facsimile: +41 41 619 7311; email: SupportPC12@pilaltusaircraft.com or from Pilatus Business 

Aircraft Ltd., Product Support 

Department, 11755 Airport Way, 

Broomfield, Colorado 80021; telephone: 

(303) 465–9099; facsimile: (303) 465–

6040. To review this service 

information, go to the National Archives 

and Records Administration (NARA). 

For information on the availability of 

this material at NARA, go to: http://

www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html or call (202) 741–

6030. 

To view the AD docket, go to the 

Docket Management Facility; U.S. 

Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

001 or on the Internet at http://

dms.dot.gov. The docket number is 

FAA–2004–18579.

FOR FURTHER INFORMATION CONTACT:

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329–

4059; facsimile: (816) 329–4090.

SUPPLEMENTARY INFORMATION: 

Discussion 

What events have caused this AD?

The Federal Office for Civil Aviation 

(FOCA), which is the airworthiness 

authority for Switzerland, recently 

notified FAA that an unsafe condition 

may exist on certain Pilatus Model PC–

7 airplanes. The FOCA reports that there 

have been 11 reports of damaged fuel 

boost pump wire leads from 9 Model 

PC–12 airplanes that have a similar type 

design. Further, the FOCA reports that 

it is possible that the wire leads to the 

left and right fuel pumps are damaged. 

This could possibly cause electrical arcs 

from the leads in an air/fuel mixture. 

What is the potential impact if FAA 

took no action? Any electrical arcing 

could lead to a fire or explosion in the 

fuel tank. 

Has FAA taken any action to this 

point? We issued a proposal to amend 

part 39 of the Federal Aviation 

Regulations (14 CFR part 39) to include 

an AD that would apply to certain 

Pilatus Model PC–7 airplanes with any 

Lear Romec RR53710B type or Lear 

Romec RR53710K fuel booster pump 

(Pilatus part number 968.84.11.401; 

968.84.11.403; or 968.84.11.404) 

installed. This proposal was published 

in the Federal Register as a notice of 

proposed rulemaking (NPRM) on 

August 20, 2004 (69 FR 516161). The 

NPRM proposed to require you to check 

the airplane logbook to determine 

whether any installed fuel booster pump 

has been modified with spiral wrap to 

protect the wire leads and has the suffix 

letter ‘‘B’’ added to the serial number of 

the fuel booster pump identification 

plate. If any installed fuel booster pump 

has not been modified, you are required 

to inspect any installed fuel booster 

pump wire lead for defects; if defects 

are found, replace the fuel booster pump 

with a modified fuel booster pump with 

spiral wrap that protects the wire leads; 

or if no defects are found, install spiral 

wrap to protect any wire leads and add 

the suffix letter ‘‘B’’ to the serial number 

of the fuel booster pump identification 

plate. The pilot is allowed to do the 

logbook check. If the pilot can positively 

determine that the fuel booster pump 

wire leads with spiral wrap are installed 

following the service information and 

that the suffix letter ‘‘B’’ is included in 

the serial number of the fuel booster 

pump identification plate, no further 

action is required.

Comments 

Was the public invited to comment?

We provided the public the opportunity 

to participate in developing this AD. We 

received no comments on the proposal 

or on the determination of the cost to 

the public. 

Conclusion 

What is FAA’s final determination on 

this issue? We have carefully reviewed 

the available data and determined that 

air safety and the public interest require 

adopting the AD as proposed except for 

minor editorial corrections. We have 

determined that these minor 

corrections:

—Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

—Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Federal Register / Vol. 69, No. 216 / Tuesday, November 9, 2004 / Rules and Regulations 64833

Changes to 14 CFR Part 39—Effect on 

the AD 

How does the revision to 14 CFR part 

39 affect this AD? On July 10, 2002, the 

FAA published a new version of 14 CFR 

part 39 (67 FR 47997, July 22, 2002), 

which governs the FAA’s AD system. 

This regulation now includes material 

that relates to altered products, special 

flight permits, and alternative methods 

of compliance. This material previously 

was included in each individual AD. 

Since this material is included in 14 

CFR part 39, we will not include it in 

future AD actions. 

Costs of Compliance 

How many airplanes does this AD 

impact? We estimate that this AD affects 

10 airplanes in the U.S. registry. 

What is the cost impact of this AD on 

owners/operators of the affected 

airplanes? We estimate the following 

costs to do the inspection:

Labor cost Parts cost Total cost

per airplane 

Total cost

on U.S. operators 

1 workhour × $65 per hour = $65 ........................................................ Not applicable ............................... $65 $65 × 10 = $650. 

We estimate the following costs to do 

any necessary replacement of any fuel 

boost pump, including the installation 

of any wire wrap, that will be required 

based on the results of the inspection. 

We have no way of determining the 

number of airplanes that may need this 

installation:

Labor cost Parts cost Total cost per airplane 

5 workhours × $65 per hour = $325 .................. $2,800 for each fuel booster pump ................. $2,800 × $325 = $3,125 for each fuel booster 

pump installation. 

Regulatory Findings 

Will this AD impact various entities?

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. 

Will this AD involve a significant rule 

or regulatory action? For the reasons 

discussed above, I certify that this AD: 

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. 

Include ‘‘Docket No. FAA–2004–18579; 

Directorate Identifier 2004–CE–19–AD’’

in your request.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, under 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. FAA amends § 39.13 by adding a 

new AD to read as follows:

2004–23–01 Pilatus Aircraft Ltd.:

Amendment 39–13856; Docket No. 

FAA–2004–18579; Directorate Identifier 

2004–CE–19–AD. 

When Does This AD Become Effective? 

(a) This AD becomes effective on December 

27, 2004. 

What Other ADs Are Affected by This 

Action? 

(b) None. 

What Airplanes Are Affected by This AD? 

(c) This AD affects Model PC–7 airplanes, 

serial numbers 101 through 618, that are:

(1) equipped with Lear Romec RR53710B 

type or Lear Romec RR53710K fuel booster 

pump, Pilatus part number (P/N) 

968.84.11.401; 968.84.11.403; or 

968.84.11.404; and 

(2) certificated in any category. 

What Is the Unsafe Condition Presented in 

This AD? 

(d) This AD is the result of mandatory 

continuing airworthiness information (MCAI) 

issued by the airworthiness authority for 

Switzerland. The actions specified in this AD 

are intended to detect and correct any defects 

in the leads of any fuel booster pump, which 

could result in electrical arcing. This failure 

could lead to a fire or explosion in the fuel 

tank. 

What Must I Do To Address This Problem? 

(e) To address this problem, you must do 

the following:

Actions Compliance Procedures 

(1) Check the airplane logbook to to ensure 

that any fuel booster pump (part number (P/

N) 968.84.11.401; 968.84.11.403; or 

968.84.11.404) has been modified with spiral 

wrap to protect the wire leads and has the 

suffix letter ‘‘B’’ added to the serial number of 

the fuel booster pump identification plate as 

required by paragraph (e)(5) of this AD.

Within 50 hours time-in-service (TIS) after December 27, 2004 (the effective date of this 

AD), unless already done.

The owner/operator holding at least a private 

pilot certificate as authorized by section 

43.7 of the Federal Aviation Regulations 

(14 CFR 43.7) may perform this check. 

64834 Federal Register / Vol. 69, No. 216 / Tuesday, November 9, 2004 / Rules and Regulations 

Actions Compliance Procedures 

(2) If you can positively determine that any fuel 

booster pump (P/N 968.84.11.401; 

968.84.11.403; or 968.84.11.404) has been 

modified following the Accomplishment Instructions—Aircraft section in Pilatus PC–7 

Service Bulletin No. 28–009, dated October 

6, 2003, and has the suffix letter ‘‘B’’ added 

to the serial number of the fuel booster pump 

identification plate as required by paragraph 

(e)(5) of this AD, then no further action is required.

Not Applicable .................................................. Make logbook entry. 

(3) Inspect any fuel booster pump (P/N 

968.84.11.401; 968.84.11.403; or 

968.84.11.404) leads for any defects.

Within 50 hours TIS after December 27, 2004 

(the effective date of this AD), unless already done.

Follow the Accomplishment Instructions—Aircraft section in Pilatus PC–7 Service Bulletin No. 28–009, dated October 6, 2003. 

This subject is also addressed in the Pilatus 

PC–7 Airplane Maintenance Manual. 

(4) If any defect is found during the inspection 

required by paragraph (e)(3) of this AD, replace the fuel booster pump.

Before further flight after the inspection required by paragraph (e)(3) of this AD in 

which any defect is found.

Follow the Accomplishment Instructions—Aircraft section in Pilatus PC–7 Service Bulletin No. 28–009, dated October 6, 2003. 

This subject is also addressed in the Pilatus 

PC–7 Airplane Maintenance Manual. 

(5) If no defects are found during the inspection 

required by paragraph (e)(3) of this AD, modify any fuel booster pump (P/N 

968.84.11.401; 968.84.11.403; or 

968.84.11.404) by installing the lead inspection by using a spiral wrap. After doing the 

modification, re-identify the fuel booster pump 

(P/N 968.84.11.401; 968.84.11.403; or 

968.84.11.404) by adding the suffix letter ‘‘B’’

to the serial number of the fuel booster pump 

identification plate.

Before further flight after the inspection required by paragraph (e)(3) of this AD where 

no defect is found.

Follow the Accomplishment Instructions—Aircraft section in Pilatus PC–7 Service Bulletin No. 28–009, dated October 6, 2003. 

This subject is also addressed in the Pilatus 

PC–7 Airplane Maintenance Manual. 

(6) Do not install any fuel booster pump (P/N 

968.84.11.401; 968.84.11.403; or 

968.84.11.404) that has not been modified 

and identified with the suffix letter ‘‘B’’ to the 

serial number of the fuel booster pump identification plate.

As of December 27, 2004 (the effective date 

of this AD).

Follow the Accomplishment Instructions—

Spares section in Pilatus PC–7 Service Bulletin No. 28–009, dated October 6, 2003. 

Note 1: The FAA recommends that you 

incorporate Pilatus PC–7 Maintenance 

Manual No. 28–20–03, dated November 30, 

2003, and Pilatus PC–7 Maintenance Manual 

No. 12–10–01, dated November 30, 2003, in 

the appropriate section of the airplane 

maintenance manual. 

Note 2: Wiring defects are addressed in 

paragraph 11–97 in FAA Advisory Circular 

(AC) 43.13–1B. 

May I Request an Alternative Method of 

Compliance? 

(f) You may request a different method of 

compliance or a different compliance time 

for this AD by following the procedures in 14 

CFR 39.19. Unless FAA authorizes otherwise, 

send your request to your principal 

inspector. The principal inspector may add 

comments and will send your request to the 

Manager, Standards Office, Small Airplane 

Directorate, FAA. For information on any 

already approved alternative methods of 

compliance, contact Doug Rudolph, 

Aerospace Engineer, FAA, Small Airplane 

Directorate, 901 Locust, Room 301, Kansas 

City, Missouri 64106; telephone: (816) 329–

4059; facsimile: (816) 329–4090. 

Is There Other Information That Relates to 

This Subject? 

(g) Swiss AD Number HB–2004–210, issue 

dated June 11, 2004, also addresses the 

subject of this AD. 

Does This AD Incorporate Any Material by 

Reference? 

(h) You must do the actions required by 

this AD following the instructions in Pilatus 

PC–7 Service Bulletin No. 28–009, dated 

October 6, 2003. 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. To get a copy of this service 

information, contact Pilatus Aircraft Ltd., 

Customer Liaison Manager, CH–6371 Stans, 

Switzerland; telephone: +41 41 619 6208; 

facsimile: +41 41 619 7311; e-mail: 

SupportPC12@pilaltus-aircraft.com or from 

Pilatus Business Aircraft Ltd., Product 

Support Department, 11755 Airport Way, 

Broomfield, Colorado 80021; telephone: (303) 

465–9099; facsimile: (303) 465–6040. To 

review copies of this service information, go 

to the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, go 

to: http://www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html or call (202) 741–6030. To 

view the AD docket, go to the Docket 

Management Facility; U.S. Department of 

Transportation, 400 Seventh Street, SW., 

Nassif Building, Room PL–401, Washington, 

DC 20590–001 or on the Internet at http://

dms.dot.gov. The docket number is FAA–

2004–18579.

Issued in Kansas City, Missouri, on 

October 29, 2004. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–24717 Filed 11–8–04; 8:45 am] 

BILLING CODE 4910–13–P