This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

6191 

Vol. 71, No. 25 

Tuesday, February 7, 2006 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20440; Directorate 

Identifier 2005–CE–05–AD; Amendment 39– 

14472; AD 2006–03–08] 

RIN 2120–AA64 

Airworthiness Directives; Aero 

Advantage ADV200 Series (Part 

Numbers ADV211CC and ADV212CW) 

Vacuum Pumps 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for all 

airplanes equipped with Aero 

Advantage ADV200 series (part numbers 

ADV211CC and ADV212CW) vacuum 

pumps installed under supplemental 

type certificate number SA10126SC, 

through field approval, or other 

methods. This AD requires you to 

remove from service any affected 

vacuum pump and install an FAAapproved vacuum pump other than the 

affected part numbers. This AD results 

from several reports of pump chamber 

failure. We are issuing this AD to 

prevent vacuum pump failure or 

malfunction during instrument flight 

rules (IFR) flight that could lead to loss 

of flight instruments critical for flight. 

The loss of flight instruments could 

cause pilot disorientation and loss of 

control of the aircraft. 

DATES: This AD becomes effective on 

March 10, 2006. 

As of March 10, 2006, the Director of 

the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation. 

ADDRESSES: 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–2005–20440; Directorate Identifier 

2005–CE–05–AD. 

FOR FURTHER INFORMATION CONTACT: 

Peter Hakala, Aerospace Engineer, 

Special Certification Office, Rotorcraft 

Directorate, FAA, 2601 Meacham 

Boulevard, Fort Worth, Texas 76193– 

0190; telephone: (817) 222–5145; 

facsimile: (817) 222–5785. 

SUPPLEMENTARY INFORMATION: 

Discussion 

What events have caused this AD? For 

the Aero Advantage ADV200 series (part 

numbers (P/Ns) ADV211CC and 

ADV212CW) vacuum pumps, FAA has 

received reports of 14 single-shaft 

failures and 11 dual-shaft failures in a 

population of 285 pumps. Nine of the 

failures occurred with less than 100 

hours time-in-service. 

In May 2004, Aero Advantage 

reported to FAA that they had stopped 

production and sales of the pumps, and 

they were quitting the business. 

The Aero Advantage ADV200 series 

vacuum pumps are installed under 

supplemental type certificate number 

SA10126SC, through field approval, or 

other methods. The installation of the 

vacuum pump includes a monitor 

system, AFMS, and a placard. 

What is the potential impact if FAA 

took no action? Failure or malfunction 

of the vacuum pump during IFR flight 

could lead to loss of flight instruments 

critical for flight. The loss of flight 

instruments could cause pilot 

disorientation and loss of control of the 

aircraft. 

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 all airplanes 

equipped with Aero Advantage ADV200 

series (part numbers ADV211CC and 

ADV212CW) vacuum pumps installed 

under supplemental type certificate 

number SA10126SC, through field 

approval, or other methods. This 

proposal was published in the Federal 

Register as a notice of proposed 

rulemaking (NPRM) on May 11, 2005 

(70 FR 24731). The NPRM proposed to 

require you to remove any affected 

vacuum pump and related monitor 

system, remove the applicable AFMS 

and placard, and install an FAAapproved vacuum pump other than the 

affected part numbers. 

Comments 

Was the public invited to comment? 

We provided the public the opportunity 

to participate in developing this AD. 

The following presents the comments 

received on the proposal and FAA’s 

response to each comment: 

Comment Issue No. 1: Allow the 

Vacuum Pump Monitoring System To 

Remain Installed 

What is the commenter’s concern? 

Forty commenters recommend that the 

vacuum pump monitoring system be 

allowed to remain in their airplanes. 

Several of the commenters point out 

that the vacuum pump warning system 

can easily be adapted to operate with a 

replacement FAA-approved vacuum 

pump. In general, the commenters feel 

that the vacuum pump monitoring 

system enhanced safety by letting the 

pilot know if the vacuum pump was not 

working. 

What is FAA’s response to the 

concern? The FAA agrees with the 

commenters that the vacuum pump 

monitoring system enhances safety. 

However, the pump monitoring system 

is optional equipment and its 

installation does not address the unsafe 

condition. Phoenix Group Service 

Bulletin Number 05–01, dated 

November 22, 2005, gives instructions 

to operators for the hook-up and usage 

of the vacuum monitoring system now 

installed. 

We will change the final rule to 

eliminate the mandatory removal of the 

vacuum pump monitoring system and 

allow the optional use of the existing 

monitoring system. 

Comment Issue No. 2: Limit the 

Effectivity of the Final Rule to 

Airplanes With Installation of the 

Lycoming Engines (Lycoming) IO–540 

Series Engines 

What is the commenter’s concern? 

Eleven commenters state that the final 

rule should only apply to airplanes with 

installation of the Lycoming IO–540 

series reciprocating engines. We infer 

from the comments received that the 

commenters conclude that failures of 

the vacuum pump system occur only on 

airplanes with installation of the 

Lycoming IO–540 series engines. 


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6192 Federal Register / Vol. 71, No. 25 / Tuesday, February 7, 2006 / Rules and Regulations 

What is FAA’s response to the 

concern? We disagree with the 

comments that the final rule should 

only apply to airplanes with installation 

of the Lycoming IO–540 series engines. 

The Aero Advantage vacuum pumps, 

part numbers ADV211CC and 

ADV212CW, use the same internal 

components and could be installed on a 

six-cylinder or a four-cylinder engine. 

The only difference in the two models 

is that one runs clockwise, while the 

other runs counterclockwise. Failures of 

the Aero Advantage vacuum pumps 

have been reported in both four-cylinder 

and six-cylinder engine installations. 

Therefore, a chance of a vacuum pump 

failure also exists with the four-cylinder 

installations. 

We are not changing the final rule as 

a result of these comments. 

Comment Issue No. 3: Estimated Work 

Hours Required for the Removal and 

Replacement of the Aero Advantage 

Vacuum Pump 

What is the commenter’s concern? 

One commenter, an owner of an 

airplane with a Continental E185–8 

engine installation, comments that 5 

work hours should be allotted for the 

removal of the existing pump and 

warning system and the replacement 

with another FAA-approved vacuum 

pump. 

What is FAA’s response to the 

concern? The FAA is not revising the 

Cost Impact section based on the 

clarification in the final rule that the 

current monitoring system is optional 

equipment and its installation does not 

cause or contribute to the unsafe 

condition. Therefore, we believe that 

our original estimate of three work 

hours is realistic. 

We are not changing the final rule as 

a result of this comment. 

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 

the changes discussed above and minor 

editorial corrections. We have 

determined that these changes and 

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. 

Docket Information 

Where can I go to view the docket 

information? You may view the AD 

docket that contains information 

relating to this subject in person at the 

DMS Docket Offices between 9 a.m. and 

5 p.m. (eastern time), Monday through 

Friday, except Federal holidays. The 

Docket Office (telephone 1–800–647–

5227) is located on the plaza level of the 

Department of Transportation NASSIF 

Building at the street address stated in 

ADDRESSES. You may also view the AD 

docket on the Internet at http:// 

dms.dot.gov. 

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 

285 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 this removal and 

replacement. We have no way of 

determining the exact number of 

airplanes that will need this removal 

and replacement: 

Labor cost Average parts 

cost 

Total cost per 

airplane 

3 work hours × $65 = $195 ..................................................................................................................................... $400 $595 

Authority for This Rulemaking 

What authority does FAA have for 

issuing this rulemaking action? Title 49 

of the United States Code specifies the 

FAA’s authority to issue rules on 

aviation safety. Subtitle I, Section 106 

describes the authority of the FAA 

Administrator. Subtitle VII, Aviation 

Programs, describes in more detail the 

scope of the agency’s authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this AD. 

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 other 

information as included in the 

Regulatory Evaluation) 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–2005–20440; 

Directorate Identifier 2005–CE–05–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: 


dsatterwhite on PROD1PC65 with RULES
Federal Register / Vol. 71, No. 25 / Tuesday, February 7, 2006 / Rules and Regulations 6193 

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: 

2006–03–08 Aero Advantage: Amendment 

39–14472; Docket No. FAA–2005–20440; 

Directorate Identifier 2005–CE–05–AD. 

When Does This AD Become Effective? 

(a) This AD becomes effective on March 10, 

2006. 

What Other ADs Are Affected by This 

Action? 

(b) None. 

What Airplanes Are Affected by This AD? 

(c) This AD affects ADV200 series (part 

numbers (P/Ns) 

ADV211CC and ADV212CW) vacuum 

pumps installed on, but not limited to, the 

following aircraft that are certificated in any 

category. These vacuum pumps can be 

installed under supplemental type certificate 

number SA10126SC, through field approval, 

or other methods: 

Make Model 

Alexandria Aircraft, LLC ................................ 14–19, 14–19–2, 14–19–3, 17–30, 17–31, 17–31TC, 17–30A, 17–31A, and 17–31ATC. 

Alliance Aircraft Group, LLC ......................... H–295 (USAF U10D). 

American Champion Aircraft Corp. ............... 7AC, 7ECA, 7GC, 7GCA, 7GCAA, 7GCB, 7GCBC, 7HC, 7KC, 7KCAB, 8GCBC, and 8KCAB. 

Cessna Aircraft Company, The ..................... 172, 172A, 172B, 172C, 172D, 172E, 172F, 172G, 172H, 172I, 172K, 172L, 172M, 172N, 172P, 

172Q, 182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 

182N, 182P, 182Q, 182R, R182, T182, TR182, 172RG, R172E, R172F, R172H, R172J, 152, 

A152, 210, 210–5 (205), 210–5A (205A), 210A, 210B, 210C, 210D, 210E, 210F, 210G, 210H, 

210J, 210K, 210L, 210M, 210N, P210N, T210G, T210H, T210M, T210N, T210R, 185, 185A, 

185B, 185C, 185D, 185E, 180, 180A, 180B, 180C, 180D, 180E, 180F, 180G, 180H, 180J, 120, 

140, 170, 170A, 170B, 177, 177A, 177B, 207, 207A, T207, T207A, 177RG, 206, P206, P206A, 

P206B, P206C, P206D, P206E, TP206A, TP206B, TP206C, TP206D, TP206E, TU206A, 

TU206B, TU206C, TU206D, TU206E, TU206F, TU206G, U206, U206A, U206B, U206C, 

U206D, U206E, U206F, U206G, 188, 188A, 188B, A188, A188A, and A188B. 

Commander Aircraft Company ...................... 112, 112B, 112TC, 114, and 114A. 

Dynac Aerospace Corporation ...................... Aero Commander 100. 

Global Amphibians, LLC ............................... Lake LA–4–200, Lake Model 250. 

Maule Aerospace Technology, Inc. ............... M–4–210, M–4–220, M–5–180C, M–5–200, M–5–235C, M–6–180, and M–6–235. 

Mooney Aircraft Corporation ......................... M20, M20A, M20B, M20C, M20D, M20E, M20F, M20G, M20J, M20K, M20M, and M22. 

Navion Aircraft Company, Ltd. ...................... Navion G and Navion H. 

Piper Aircraft, Inc., The New ......................... PA–23, PA–23–160, PA–23–235, PA–23–250 (Navy UO–1), PA–E23–250, PA–24, PA–24–250, 

PA–24–260, PA–18, PA–18–105 (Special), PA–18–135, PA–18–150, PA–20–115, PA–20–135, 

PA–22–108, PA–22–135, PA–22–150, PA–22–160, PA–25, PA–25–235, PA–25–260, PA–28– 

140, PA–28–150, PA–28–151, PA–28–160, PA–28–161, PA–28–180, PA–28–181, PA–28– 

201T, PA–28–235, PA–28–236, PA–28R–180, PA–28R–200, PA–28R–201, PA–28R–201T, 

PA–28RT–201, PA–28RT–201T, PA–25, PA–25–235, PA–25–260, J5A–80, J5A (Army L–4F), 

J5B (Army L–4G), J5C, PA–12, PA–36–285, PA–36–300, PA–36–375, PA–38–112, PA–30, 

PA–39, PA–40, PA–31, PA–31–300, PA–31–325, PA–31–350, PA–32–260, PA–32–300, PA– 

32–301, PA–32–301T, PA–32R–300, PA–32R–301 (HP), PA–32R–301T, PA–32RT–300T, PA– 

31P, and PA–36–300. 

Raytheon Aircraft Company .......................... 35–33, 35–A33, 35–B33, 35–C33, 35–C33A, 36, A36, A36TC, B36TC, E33, E33A, E33C, F33, 

F33A, F33C, G33, H35, J35, V35, V35A, V35B, D45 (Military T–34B), 35, 35R, A35, B35, C35, 

D35, E35, F35, G35, 19A, 23, A23, A23A, A24, A24R, B19, B23, B24R, C23, and C24R. 

Rogers, Burl A. .............................................. 15AC and S15AC. 

SOCATA—Groupe Aerospatiale ................... MS 885, MS 892A–150, MS 892E–150, MS 893A, MS 893E, Rallye 150 ST, Rallye 150 T, TB 10, 

TB 20, and TB 9 

Tiger Aircraft LLC .......................................... AA–1, AA–1A, AA–1B, AA–1C, AA–5, AA–5A, and AA–5B. 

What Is the Unsafe Condition Presented in 

This AD? 

(d) This AD is the result of several reports 

of pump chamber failure. The actions 

specified in this AD are intended to prevent 

the vacuum pump failure or malfunction 

during instrument flight rules (IFR) flight that 

could lead to loss of flight instruments 

critical for flight. The loss of flight 

instruments could cause pilot disorientation 

and loss of control of the aircraft. 

What Must I Do To Address This Problem? 

(e) To address this problem, you must do 

the following: 

Actions Compliance Procedures 

(1) Remove from service any Areo Advantage 

ADV200 series (P/Ns ADV211CC and 

ADV212CW) vacuum pump.

Within 100 hours time-in-service (TIS) or the 

next 12 calendar months after March 10, 

2006 (the effective date of this AD), whichever occurs first, unless already done.

Not Applicable. 

(2) Install an FAA-approved vacuum pump that 

is not an Aero Advantage ADV200 series 

vacuum pump. 

Prior to further flight after removing any Aero 

Advantage ADV200 series vacuum pump.

Not Applicable. 


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6194 Federal Register / Vol. 71, No. 25 / Tuesday, February 7, 2006 / Rules and Regulations 

Actions Compliance Procedures 

(3) If you choose not to utilize the Aero Advantage vacuum pump monitoring system per 

STC SA10126SC, then do the following: 

(i) Remove the Airplane Flight Manual Supplement (AFMS) for STC SA10126SC 

and the placard for the vacuum pump 

monitoring system. 

(ii) Complete the appropriate logbook entry 

and Form 337 to show that the airplane 

is no longer equipped with STC 

SA10126SC. 

Prior to further flight after removing any Aero 

Advantage ADV200 series vacuum pump.

Not Applicable. 

(4) If you choose to utilize the Aero Advantage 

vacuum pump monitoring system per STC 

SA10126SC, then do the following: 

(i) Connect the replacement vacuum pump 

to the vacuum pump monitoring system. 

(ii) Make the following notation to the front 

of the AFMS for STC SA10126SC: ‘‘The 

Aero Advantage vacuum pump was removed to comply with AD 2005–**–**, 

and this AFMS now gives instructions for 

the operation of the vacuum pump monitoring system with a replacement vacuum pump.’’

(iii) Attach a copy of the Phoenix Group 

Service Bulletin No. 05–01, dated November 22, 2005, to the AFMS for STC 

SA10126SC. 

Prior to further flight after removing any Aero 

Advantage ADV200 series vacuum pump.

Connect the vacuum pump monitoring system 

with the procedures in Phoenix Group, 

Service Bulletin No. 05–01, dated November 22, 2005. 

(5) Do not install any Aero Advantage ADV200 

series (P/Ns ADV211CC and ADV212CW) 

vacuum pump. 

As of March 10, 2006 (the effective date of 

this AD).

Not Applicable. 

May I Request an Alternative Method of 

Compliance? 

(f) The Manager, Special Certification 

Office, Rotorcraft Directorate, FAA, has the 

authority to approve alternative methods of 

compliance for this AD, if requested using 

the procedures found in 14 CFR 39.19. For 

information on any already approved 

alternative methods of compliance, contact 

Peter Hakala, Aerospace Engineer, Special 

Certification Office, Rotorcraft Directorate, 

FAA, 2601 Meacham Boulevard, Fort Worth, 

Texas 76193–0190; telephone: (817) 222–

5145; facsimile: (817) 222–5785. 

May I Get Copies of the Document 

Referenced in This AD? 

(g) If you choose to utilize the vacuum 

pump monitoring system, you must connect 

the replacement vacuum pump with the 

instructions in Phoenix Group, Service 

Bulletin No. 05–01, dated November 22, 

2005. 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 

Phoenix Group, 9608 Taxiway Dr., Granbury, 

TX 76049; e-mail: 

phoenixgroup2@yahoo.com. 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–

200520440; Directorate Identifier 2005–CE–

05–AD. 

Issued in Kansas City, Missouri, on January 

26, 2006. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 06–957 Filed 2–6–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22875; Directorate 

Identifier 2005–NM–179–AD; Amendment 

39–14469; AD 2006–03–05] 

RIN 2120–AA64 

Airworthiness Directives; Short 

Brothers Model SD3–60 SHERPA, 

SD3–SHERPA, and SD3–60 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to all Short Brothers 

Model SD3–60 and SD3-SHERPA 

airplanes. That AD currently requires an 

inspection of the fork end of the rear 

pintle pin on each main landing gear 

(MLG) to verify that sealant is properly 

applied and is undamaged, and related 

investigative/corrective actions if 

necessary. This new AD requires an 

additional inspection for correctly 

applied sealant on the MLG rear pintle 

pin assemblies, and related 

investigative/corrective actions if 

necessary. This AD also expands the 

applicability of the existing AD. This 

AD results from a new report of a 

cracked pintle pin fork end. We are 

issuing this AD to prevent stresscorrosion cracking and subsequent 

failure of the MLG. 

DATES: This AD becomes effective 

March 14, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of March 14, 2006. 

On March 18, 1993 (58 FR 7983, 

February 11, 1993), the Director of the 

Federal Register approved the 

incorporation by reference of Shorts 

SD3–60 Service Bulletin SD360–32–33, 

dated August 7, 1992. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 


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