` 

FEDERAL AVIATION ADMINISTRATION 

AIRWORTHINESS DIRECTIVES 

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, 

BALLOONS, & AIRSHIPS 

BIWEEKLY 2005-21 

This electronic copy may be printed and used in lieu of the FAA biweekly paper copy. 

U.S. Department of Transportation 

Federal Aviation Administration 

Regulatory Support Division 

Delegation and Airworthiness Programs Branch, AIR-140 

P. O. Box 26460 

Oklahoma City, OK 73125-0460 

FAX 405-954-4104
2 
SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 

AD No. Information Manufacturer Applicability 

Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information; 

3 

Biweekly 2005-01 

2004-26-09 Rolls-Royce Corporation Engine: 250-B17, -B17B, -B17C, -B17D, -B17E, 250-C20, -C20B, 

-C20F, -C20J, -C20S, and -C20W Series Turboprop and 

Turboshaft 

2004-26-11 Bell Helicopter Textron Canada Rotorcraft: 222, 222B, 222U, 230, 430 

2005-01-04 S 98-15-13 Raytheon Aircraft Company 65-90, 65-A90, B90, C90, C90A, C90B, E90, F90, H90, 100, 

A100, A100-1, (RU-21J), B100, 200, 200C, 200CT, 200T, A200, 

A200C, A200CT, B200, B200C, B200CT, B200T, 300, B300, 

B300C, 99, 99A, A99,, A99A, B99, C99 

2005-01-10 S 74-06-01 The New Piper Aircraft, Inc PA-23-235, PA-23-250, and PA-E23-250 

2005-01-11 Pilatus Aircraft Ltd. PC-12 and PC-12/45 

Biweekly 2005-02 

98-20-38 R1 R Raytheon Aircraft Company Beech 200 (A100-1 (U-21J)), Beech 200C, Beech 200CT, Beech 

200T, Beech A200 (C-12A) or (C-12C), Beech A200C (UC-12B), 

Beech A200CT (C-12D), (FWC-12D), (RC-12D), (C-12F), 

(RC-12G), (RC-12H), (RC-12K), or (RC-12P), B200CT, and 

B200T 

2005-01-14 S 2002-21-16 Bombardier-Rotax GmbH Engine: 912 F, 912 S, and 914 F Series Reciprocating 

2005-01-17 S 98-03-14 EXTRA Flugzeugbau GmbH EA–300 and EA–300/S 

2005-01-18 S 93-25-07 Raytheon Aircraft Company A100–1 (U–21J), 200, B200, A200 (C–12A), A200 (C–12C), 

A200C (UC–12B), A200CT (C–12D), A200CT (FWC–12D), 

A200CT (RC–12D), A200CT (C–12F), A200CT (RC–12G), 

A200CT (RC–12H), A200CT (RC–12K), A200CT (RC–12P), 

A200CT (RC–12K), 200C, B200C, 200CT, 200T, B200C (C-12F), 

B200C (UC–12F), B200C (UC–12M), B200CT, 300, B300, 

B300C, and B300C 

2005-01-19 S 2004-10-15 GARMIN International Inc Appliance: GTX 33, GTX 33D, GTX 330, and GTX 330D Mode S 

Transponders 

2005-02-01 The Lancair Company LC40–550FG and LC42–550FG 

Biweekly 2005-03 

2005-01-04 COR 

S 98-15-13 

Raytheon Aircraft Company 65–90, 65–A90, B90, C90, C90A, E90, F90, H90, 100, A100, 

A100–1 (RU–21J), B100, 200, 200C, 200CT, 200T, A200, 

A200C, A200CT, B200, B200C, B200CT, B200T, 300, B300, 

B300C, 99, 99A, A99, A99A, B99, and C99 

2005-01-18 COR 

S 93-25-07 

Raytheon Aircraft Company A100–1 (U–21J), 200, B200, A200 (C–12A), A200 (C–12C), 

A200C (UC–12B), A200CT (C–12D), A200CT (FWC–12D), 

A200CT (RC–12D), A200CT (C–12F), A200CT (RC–12G), 

A200CT (RC–12H), A200CT (RC–12K), A200CT (RC–12P), 

A200CT (RC–12K), 200C, B200C, 200CT, B200CT, 200T, 

B200T, B200C (C–12F), B200C (UC–12F), B200C (UC–12M), 

B200CT, 300, B300C, and B300C 

2005-02-11 COR Gippsland Aeronautics Pty. Ltd. GA8 

2005-03-04 Pacific Aerospace Corp., Ltd. 750XL 

Biweekly 2005-04 

2005-01-04 COR 

S 98-15-13 

Raytheon Aircraft Company 65–90, 65–A90, B90, C90, C90A, E90, F90, H90, 100, A100, 

A100–1 (RU–21J), B100, 200, 200C, 200CT, 200T, A200, 

A200C, A200CT, B200, B200C, B200CT, B200T, 300, B300, 

B300C, 99, 99A, A99, A99A, B99, C99 

2005-03-07 Bell Helicopter Textron Canada Rotorcraft: 407 

2005-03-08 Eurocopter France Rotorcraft: AS350B, BA, B1, B2, B3, C, D, D1, and EC130 B4 

2005-03-09 Eurocopter France Rotorcraft: EC 155B, EC155B1, SA-360C, SA-365C, SA-365C1, 

SA-365C2, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and 

SA-366G1 

2005-03-10 S 2002-08-54 Bell Helicopter Textron Rotorcraft: 222, 222B, 222U, and 230 

2005-04-09 S 2004-26-11 Bell Helicopter Textron Canada Rotorcraft: 222, 222B, 222U, 230, and 430 
SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 

AD No. Information Manufacturer Applicability 

Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information; 

4 

Biweekly 2005-05 

2005-04-08 Hartzell Propeller Inc. Propeller: HC-B3TN-5( )/T10282( ) 

2005-04-10 General Electric Company Engine: CT58-140-1, CT58-140-2, and surplus military T58-GE-5, 

-10, -100, and ''402 turboshaft 

2005-04-16 Pilatus Aircraft Ltd. PC-12 and PC-12/45 

2005-05-51 E Cessna Aircraft Company 402C and 414A 

2005-05-52 E, S 2005-05-51 Cessna Aircraft Company 402C and 414A 

2005-05-53 E Cessna Aircraft Company 172R, 172S, 182T, and T182T 

2005-05-53 R1 E, R, S 2005-05-

53 

Cessna Aircraft Company 172R, 172S, 182T, and T182T 

Biweekly 2005-06 

2005-05-14 Eagle Aircraft (Malaysia) Eagle 150B 

2005-05-15 Honeywell International Inc. Engine: TFE731-2 and -2C series, and TFE731-3, -3A, -3AR, -3B, 

-3BR, and -3R series turbofan 

2005-06-01 Eurocopter France Rotorcraft: EC 155B and EC 155B1 

Biweekly 2005-07 

2005-05-52 FR, S 2005-05-51 

and 2000-23-01 

Cessna 402C and 414A 

2005-05-53 R1 R, 2005-05-53 Cessna 172R, 172S, 182T, and T182T 

2005-06-13 S 99-0602 Fairchild Aircraft, Inc. SA226-AT, SA226-TC, SA226-T, SA226-T(B), SA227-TT, 

SA227-TT(300), SA227-AC, SA227-AT, SA227-BC, and SA227-

CC/DC 

2005-07-01 Cessna 208 and 208B 

Biweekly 2005-08 

83-08-01 R2 R, S 83-08-01 R1 Hartzell Propeller Inc. Propeller: HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC-B4TN-3, 

HC-B4TN-5, HC-B4MN-5, and HC-B5MP-3 turbopropellers 

2005-07-01 COR Cessna 208 and 208B 

2005-07-27 S 2000-18-04 Aviointeriors S.p.A. Appliance: Model 312 Seats 

Biweekly 2005-09 

2005-08-06 Centrair Glider: 101, 101A, 101AP, and 101P 

2005-08-07 Pilatus Aircraft Limited Sailplane: B4-PC11, B4-PC11A, and B4-PC11AF 

2005-08-12 Centrair Glider: 101, 101A, 101AP, and 101P 

2005-08-13 Glaser-Dirks Flugzeugbau 

GmbH 

Sailplane: DG-800B 

2005-08-14 LET a.s. Sailplane: Blanik L-13 AC 

2005-09-51 E Turbomeca S.A. Engine: Arrius 2F Turboshaft 

Biweekly 2005-10 

2004-25-16 R1 R, 2004-25-16 Kelly Aerospace Power Systems Appliance: Fuel regulator shutoff valve 

2005-08-06 COR Centrair Glider: 101 Series 

2005-09-05 Eurocopter France Rotorcraft: EC120B 

2005-09-06 Agusta S.p.A. Rotorcraft: A119 

2005-09-07 Agusta S.p.A. Rotorcraft: A109E 
SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 

AD No. Information Manufacturer Applicability 

Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information; 

5 

Biweekly 2005-11 

2005-09-51 FR Turbomeca S.A. Engine: Arrius 2F turboshaft 

2005-10-12 Schweizer Aircraft Corporation Rotorcraft: 269C, C-1, and D 

2005-10-13 Rolls-Royce Corporation Engine: 250-B17B, -B17C, -B17D, -B17E, -C20, -C20B, -C20F, -

C20J, -C20S, and -C20W turboprop and turboshaft 

2005-10-14 S 2004-01-51 Eurocopter France Rotorcraft: AS355E, F, F1, F2, and N 

2005-10-23 DG Flugzeubau GmbH and 

Glaser-Dirks Flugzeubau GmbH 

Glider:DG-500MB and DG-800B 

2005-10-24 S 2003-14-20 AeroSpace Technologies of 

Australia Pty. Ltd. 

N22B, N22S and N24A 

2005-11-01 Turbomeca S.A. Engine: Arrius 1A turboshaft 

Biweekly 2005-12 

2005-11-05 Precise Flight, Inc. Appliance: Standby vacuum system (SVS) 

2005-11-06 Pilatus Aircraft Ltd. PC-12 and PC-12/45 

2005-11-07 Extra Flugzeugproduktions-Und 

Vertriebs-GmbH 

EA-300, EA-300S, ES-300L, and EA-300/200 

2005-11-08 GROB-WERKE G120A 

2005-12-01 Agusta S.p.A. Rotorcraft: A109E 

2005-12-02 S 98-10-12 Revo, Incorporated Colonial C-2, Lake LA-4, Lake LA-4A, Lake LA-4P, and Lake 

LA-4-200 

2005-12-51 E Rockwell International and 

Autair Ltd. 

AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B, AT-6C (SNJ-4), AT-6D 

(SNJ-5), AT-6F (SNJ-6), BC-1A, Harvard (Army AT-16), SNJ-7, 

and T-6G 

Biweekly 2005-13 

2005-12-03 Sikorsky Aircraft Corporation Rotorcraft: S-92A 

2005-12-06 S 96-12-07 Teledyne Continental Motors Appliance: S-20, S-1200, D-2000, and D-3000 Series Magnetos 

2005-12-08 Turbomeca S.A. Engine: Arrius 2 B1, 2 B1A, 2 B1A-1, and 2 B2 turboshaft 

2005-12-09 Grob-Werke G120A 

2005-12-12 S 79-10-15 Cessna Aircraft Company 401, 401A, 401B, 402, 402A, 402B, 411, and 411A 

2005-12-13 S 2005-05-52 Cessna Aircraft Company 402C and 414A 

2005-12-20 The Lancair Company LC41-550FG 

2005-12-51 FR Rockwell International AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B, AT-6C (SNJ-4), AT-6D 

(SNJ-5), AT-6F (SNJ-6), BC-1A, Harvard (Army AT-16), SNJ-7, 

and T-6G 

2005-13-01 S 2004-18-01 Hoffmann Propeller GmbH & 

Co KG 

Propeller: HO-V343 and HO-V343K 

2005-13-07 Honeywell International Inc. Engine: TFE731-2 and -3 series turbofan 

2005-13-09 GROB-WERKE G120A 

2005-13-10 Cessna Aircraft Company 172R, 172S, 182T, T182T, 206H, T206H 

2005-13-11 General Electric Company Engine: CT64-820-4 turboprop 

2005-13-12 Air Tractor, Inc. AT–300, AT–301, AT–302, AT–400, and AT–400A, AT–

401/AT–402, AT–602, AT–802 and AT–802A 

2005-13-13 Sikorsky Aircraft Corporation Rotorcraft: S-92A 

2005-13-16 S 93-24-14 The New Piper Aircraft, Inc. PA-34-200, PA-34-200T, and PA-34-220T 

2005-13-17 Agusta. S.p.A. Rotorcraft: AB412 Series 

2005-13-23 S 2003-18-03 Eurocopter France Rotorcraft: EC 155B, EC155B1, SA-365N, SA-365N1, AS365N2, and AS 365 N3 

2005-13-25 Turbomeca S.A. Engine: Arriel 2B 

Biweekly 2005-14 

2005-12-12 COR Cessna 401, 401A, 401B, 402, 402A, 402B, 411, and 411A 

2005-12-20 COR Lancair Company LC41-550FG 
SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 

AD No. Information Manufacturer Applicability 

Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information; 

6 

Biweekly 2005-15 

2005-12-51 COR Rockwell International AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B, AT-6C (SNJ-4), AT-6D 

(SNJ-5), AT-6F (SNJ-6), BC-1A, Harvard (Army AT-16), SNJ-7, 

and T-6G 

2005-14-11 Hartzell Propeller, Inc., 

McCauley Propeller, Sensenich 

Propeller 

Propeller: See AD 

2005-14-12 Hartzell Propeller Propeller: HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC-B3MN-3, 

HC-B4TN-3, HC-B4TN-5, HC-B4MN-5, HC-B4MP-3, HCB4MP-5, and HC-B5MP-3 

Biweekly 2005-16 

2005-15-10 New Piper Aircraft PA-34-200T, PA-34-220T, PA-44-180, and PA-44-180T 

Biweekly 2005-17 

2004-14-02 COR Rolls-Royce Corporation Engine: 250-C28, -C28B, and -C28C turboshaft 

2005-16-04 Bell Helicopter Textron Rotorcraft: 206A and 206B 

2005-16-05 Robinson Helicopter Company Rotorcraft: R-22 Series 

2005-17-01 Pilatus Aircraft Ltd. PC–6, PC–6–H1, PC–6–H2, PC–6/350, PC–6/350–H1, PC–6/350–

H2, PC–6/A, PC–6/A–H1, PC–6/A–H2, PC–6/B–H2, PC–6/B1–

H2, PC–6/B2–H2, PC–6/B2–H4, PC–6/C–H2, PC–6/C1–H2 

Biweekly 2005-18

95-19-15 R1 R 95-19-15 Tiger Aircraft LLC AA–5, AA–5A, AA–5B, AG–5B 

2005-13-09 COR GROB-WERKE G120A 

2005-17-06 Turbomeca Engine: Artouste III B, B1, and D turboshaft 

2005-17-11 Cessna 525, 525A, and 525B 

2005-17-15 Turbomeca S.A. Engine: Arrius 2F turboshaft 

2005-17-17 Turbomeca S.A. Engine: Arrius 2F turboshaft 

2005-17-19 Cirrus Design Corporation SR20 and SR22 

Biweekly 2005-19

2005-18-12 Hartzell Propeller Inc. Propellers Propeller: HC–92W, BHC–92W, HC–92Z, BHC–92Z, HC–B3P, 

HC–B3R, HC–B3W, BHC–B3W, HA–B3Z, HC–B3Z Hub Model 

Series 

2005-18-20 Goodrich De-icing and Specialty 

Systems 

Appliance: P4E1188 series, P4E1601 series, P4E2200 series, 

P4E2271-10, P4E2575-7, P4E2575-10, P4E2598-10, P5855BSW, 

P6199SW, P6592SW, P6662SW, and P6975-11 

2005-18-21 Raytheon Aircraft Company 1900, 1900C, 1900C (C–12J), 1900D 

2005-18-22 Raytheon Aircraft Company 390 

2005-19-07 Raytheon Aircraft Company 390 

2005-19-10 Turbomeca Engine: Arrius 2 F turboshaft 

2005-19-11 Lycoming Engines Engine: AEIO-360, IO-360, O-360, LIO-360, LO-360, AEIO-540, 

IO-540, O-540, and TIO-540 series 

Biweekly 2005-20

2005-19-17 PZL-Swidnik S.A. Glider: PW–5 "Smyk", PW–6U 

2005-19-20 The New Piper Aircraft, Inc. PA-28-160, PA-28-161, PA-28-180, and PA-28-181 

2005-20-04 Teledyne Continental Motors Engine: GTSIO-520 series reciprocating 
SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 

AD No. Information Manufacturer Applicability 

Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information; 

7 

Biweekly 2005-21

2003-19-14 R2 R 2003-19-14 R1 BURKHART GROB LUFT–

UND RAUMFAHRT GmbH & 

CO KG 

Glider: G103 TWIN ASTIR, G103A TWIN II ACRO (aerobatic 

category), G103C TWIN III ACRO (aerobatic category) 

2005-20-11 Rolls-Royce Corporation Engine: 250-C28, -C28B, and -C28C turboshaft 

2005-20-12 S 2004-13-01 Dowty Aerospace Propellers Propeller: R321/4-82-F/8, R324/4-82-F/9, R333/4-82-F/12, and 

R334/4-82-F/13 

2005-20-24 Socata–Groupe Aerospatiale TBM 700 

2005-20-25 Cessna Aircraft Company 401, 401A, 401B, 402, 402A, 402B, 402C, 404, 411, 411A, 414, 

414A, 421, 421A, 421B, 421C, 425, 441 

2005-20-26 Aviointeriors S.p.A. Appliance: 312 box mounted seats 

2005-20-38 Bell Helicopter Textron Rotorcraft: 212, 412, and 412EP 
8 

BW 2005-21 

BURKHART GROB LUFT–UND RAUMFAHRT GmbH & CO KG

AIRWORTHINESS DIRECTIVE 

GLIDER 

REVISION 

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 

2003-19-14 R2 BURKHART GROB LUFT–UND RAUMFAHRT GmbH & CO KG:

Amendment 39-14322; Docket No. FAA-2005-20441; Directorate Identifier 2003-CE-35-AD; 

Revises AD 2003-19-14 R1, Amendment 39-13676. 

When Does This AD Become Effective? 

 (a) This AD becomes effective on November 30, 2005. 

What Other ADs Are Affected By This Action? 

 (b) This AD revises AD 2003-19-14 R1, Amendment 39-13676. 

What Sailplanes Are Affected by This AD? 

 (c) This AD affects the following sailplane models and serial numbers that are certificated in 

any category: 

Model Serial numbers 

G103 TWIN ASTIR All serial numbers. 

G103A TWIN II ACRO (aerobatic category) All serial numbers with suffix "K". 

G103C TWIN III ACRO (aerobatic category) All serial numbers. 

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 Germany. The actions specified in this AD are intended to prevent 

damage to the fuselage during limit load flight, which could result in reduced structural integrity. 

This condition could lead to loss of control of the sailplane. 

What Must I Do To Address This Problem? 

 (e) To address this problem, you must do the following: 
2003-19-14 R2 2 

9 

Actions Compliance Procedures 

(1) For G103 TWIN ASTIR sailplanes: 

(i) Re-set the airspeed indicator to the new placard limitations; 

(ii) Install the following placard: 

(iii) You may perform simple aerobatic flight (looping, steep 

turns, lazy eights, and chandelles) following the flight 

manual; and (iv) Revise the flight and maintenance manuals. 

Within the next 

25 hours timein-service (TIS) 

after November 

30, 2005 (the 

effective date 

of this AD), 

unless already 

done. 

Following GROB 

Service Bulletin 

No. MSB315–64/3, 

dated September 

14, 2004. 

(2) For G103A TWIN II ACRO (acrobatic category) and 

G103C TWIN III ACRO (acrobatic category) sailplanes: 

(i) Re-set the airspeed indicator to the new placard limitations; 

and 

(ii) Install the following placards on Model G103A TWIN II 

ACRO (aerobatic category) sailplanes: 

Within the next 

25 hours timein-service (TIS) 

after August 

12, 2004 (the 

effective date 

AD 2003–19–

14 R1), unless 

already done. 

Follow Grob 

Service Bulletin 

No. MSB315–65, 

dated September 

15, 2003. 
2003-19-14 R2 3 

10 

Actions Compliance Procedures 

(iii) Install the following placards on Model G103C TWIN III 

ACRO (aerobatic category) sailplanes: 

 

(3) For G103A TWIN II ACRO (acrobatic category) and 

G103C TWIN III ACRO (acrobatic category) sailplanes: as an 

alternative to the flight restrictions in paragraph (e)(2) of this 

AD, you may install additional stringers in the rear fuselage 

section. Installing additional stringers terminates the flight 

restrictions in paragraph (e)(2) of this AD. 

At any time 

after August 

12, 2004 (the 

effective date 

AD 2003–19–

14 R1). 

Follow Grob 

Service Bulletin 

No. OSB 315–66, 

dated October 16, 

2003, and Work 

Instruction for 

OSB 315–66, dated 

October 16, 2003. 

(4) For G103A TWIN II ACRO (acrobatic category) and 

G103C TWIN III ACRO (acrobatic category) sailplanes: only if 

you installed the additional stringers specified in paragraph 

(e)(3) of this AD, do the following: 

(i) Remove the placard prohibiting all aerobatic maneuvers; 

(ii) Install the following flight limitation placard on Model 

G103A TWIN II ACRO (aerobatic category) sailplanes: 

Prior to further 

flight after 

doing the 

actions in 

paragraph 

(e)(3) of this 

AD. 

Follow Grob 

Service Bulletin 

No. OSB 315–66, 

dated October 16, 

2003. 
2003-19-14 R2 4 

11 

Actions Compliance Procedures 

(iii) Install the following flight limitation placard on Model 

G103C TWIN III ACRO (aerobatic category) sailplanes: 

 

Note: The placard information in this AD is different from the information in the applicable 

service bulletins. This AD takes precedence over the service bulletins. You should update your 

placards to reflect the information presented in this AD. 

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 Gregory A. Davison, Aerospace 

Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329-4130; facsimile: (816) 329-4090. 

Is There Other Information That Relates to This Subject? 

 (g) German AD D-2003-231R3, dated November 9, 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 GROB Service 

Bulletin No. MSB315-64/3, dated September 14, 2004; Grob Service Bulletin No. MSB315-65, dated 

September 15, 2003; Grob Service Bulletin No. OSB 315-66, dated October 16, 2003; and Work 

Instruction for OSB 315-66, dated October 16, 2003. 

 (1) On August 12, 2004 (69 FR 34258, June 21, 2004), and in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51, the Director of the Federal Register approved the incorporation by 

reference of Grob Service Bulletin No. MSB315-65, dated September 15, 2003; Grob Service 

Bulletin No. OSB 315-66, dated October 16, 2003; and Work Instruction for OSB 315-66, dated 

October 16, 2003.
2003-19-14 R2 5 

12 

 (2) As of November 30, 2005, and in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51, the Director of the Federal Register approved the incorporation by 

reference of GROB Service Bulletin No. MSB315-64/3, dated September 14, 2004. 

 (3) To get a copy of this service information, contact GROB Luft-und Raumfahrt, 

Lettenbachstrasse 9, D-86874 Tussenhausen-Mattsies, Germany; telephone: 011 49 8268 998139; 

facsimile: 011 49 8268 998200; e-mail: productsupport@grob-aerospace.de. 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-2005-20441; Directorate 

Identifier 2003-CE-35-AD. 

 Issued in Kansas City, Missouri, on September 28, 2005. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, Aircraft Certification Service. 

[FR Doc. 05-19929 Filed 10-11-05; 8:45 am] 

BILLING CODE 4910-13-P 
13 

BW 2005-21 

ROLLS-ROYCE CORPORATION 

AIRWORTHINESS DIRECTIVE 

ENGINE 

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 

2005-20-11 Rolls-Royce Corporation (formerly Allison Engine Company, Allison Gas Turbine 

Division, and Detroit Diesel Allison): Amendment 39-14305. Docket No. FAA-2005-22534; 

Directorate Identifier 2005-NE-27-AD. 

Effective Date 

 (a) This airworthiness directive (AD) becomes effective October 18, 2005. 

Affected ADs 

 (b) None. 

Applicability 

 (c) This AD applies to Rolls-Royce Corporation (RRC) (formerly Allison Engine Company, 

Allison Gas Turbine Division, and Detroit Diesel Allison) models 250-C28, -C28B, and -C28C 

turboshaft engines. These engines are installed on, but not limited to, Bell Helicopter Textron 206L1; Eurocopter Deutschland BO 105 LS A-1; and Eurocopter Canada BO 105 LS A-3 helicopters. 

Unsafe Condition 

 (d) This AD results from reports of three failed third-stage turbine wheels and from the 

manufacturer's analysis of those failures. We are issuing this AD to prevent loss of power and 

uncommanded engine shutdown due to failure of the third-stage turbine wheel. 

Compliance 

 (e) You are responsible for having the actions required by this AD performed within the 

compliance times specified unless the actions have already been done. 

Onetime Visual Inspection 

 (f) For third-stage turbine wheels, part number (P/N) 6899383, with fewer than 3,000 hours 

time-since-new (TSN), inspect the next time the third-stage turbine wheel is directly available for 

removal, at the next turbine overhaul, or by April 30, 2007, whichever occurs sooner. 
2005-20-11 2 

14 

 (g) For third-stage turbine wheels, P/N 6899383, with 3,000 hours or more TSN, inspect 

within 300 hours or by April 30, 2007, whichever occurs sooner. 

 (h) Remove the third-stage turbine wheel and perform a onetime visual inspection of the seal 

joint in each passage between airfoils at the hub and shroud. Seal joint evidence must not be present 

within blade fillet radii. See Figure 1 of this AD for reference. 
2005-20-11 3 

15 

 (i) Remove from service any turbine wheel that has seal joint evidence present within blade 

fillet radii. 

Alternative Methods of Compliance 

 (j) The Manager, Chicago Aircraft Certification Office, has the authority to approve 

alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 

39.19. 

Related Information 

 (k) RRC Alert Service Bulletin No. CEB-A-72-2205, dated April 26, 2005, pertains to the 

subject of this AD. 

 Issued in Burlington, Massachusetts, on September 26, 2005. 

Francis A. Favara, 

Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. 

[FR Doc. 05-19693 Filed 9-30-05; 8:45 am] 

BILLING CODE 4910-13-P 
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BW 2005-21 

DOWTY AEROSPACE PROPELLERS

AIRWORTHINESS DIRECTIVE 

PROPELLER 

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 

2005-20-12 Dowty Aerospace Propellers: Amendment 39-14306. Docket No. 2001-NE-50-AD. 

Effective Date 

 (a) This airworthiness directive (AD) becomes effective October 28, 2005. 

Affected ADs 

 (b) This AD supersedes AD 2004-13-01, Amendment 39-13681. 

Applicability 

 (c) This AD applies to Dowty Aerospace Propellers Type R321/4-82-F/8, R324/4-82-F/9, 

R333/4-82-F/12, and R334/4-82-F/13 propeller assemblies with propeller hubs part number (P/N) 

660709201. These propeller assemblies are installed on, but not limited to, Construcciones 

Aeronauticas, S.A. (CASA) 212, British Aerospace Regional Aircraft Jetstream Models 3101 and 

3201, Fairchild Aircraft, Inc., Merlin IIIC, and Merlin IVC/Metro III airplanes. 

Unsafe Condition 

 (d) This AD results from a report of a hub separation on a CASA 212 airplane. We are issuing 

this AD to prevent propeller hub failure due to cracks in the hub, which could result in loss of control 

of the airplane. 

Compliance 

 (e) You are responsible for having the actions required by this AD performed within the 

compliance times specified unless the actions have already been done. 

Initial Ultrasonic Inspections 

 (f) Perform an initial ultrasonic inspection of the rear wall of the rear half of the propeller hub 

for cracks within the compliance time specified in the following Table 1. Use Appendix A of the 

applicable Dowty Mandatory Service Bulletin (MSB) listed in Table 1 of this AD. 
2005-20-12 2 

17 

TABLE 1.—APPLICABLE MSB FOR PROPELLER TYPE 

Propeller assembly 

type 

Initial inspection within the 

earlier of . . . 

Repeat inspection 

within . . . 

Applicable MSB 

(1) R334/4–82–F/13 10 flight hours (FH) time-inservice (TIS) or 20 days after 

the effective date of this AD. 

300 FH time-sincelast-inspection 

(TSLI). 

Alert MSB No. 61–

1119, Revision 4, dated 

September 14, 2005. 

(2) R321/4–82–F/8 50 FH TIS or 60 days after the 

effective date of this AD. 

1,000 FH TSLI MSB No. 61–1125, 

Revision 1, dated 

October 9, 2002. 

(3) R324/4–82–F/9 50 FH TIS or 60 days after the 

effective date of this AD. 

1,000 FH TSLI MSB No. 61–1126, 

Revision 1, dated 

October 9, 2002. 

(4) R333/4–82–F/12 50 FH TIS or 60 days after the 

effective date of this AD. 

1,000 FH TSLI MSB No. 61–1124, 

Revision 1, dated 

October 8, 2002. 

 (g) For hubs and propellers in storage, perform an initial ultrasonic inspection of the rear wall 

of the rear half of the propeller hub for cracks, before placing in service. Use Appendix A of the 

applicable Dowty MSB listed in Table 1 of this AD. 

 (h) Propeller hubs, P/N 660709201, already inspected using a Dowty MSB listed in Table 1 or 

earlier issue of those MSBs, comply with paragraph (f) of this AD. 

Repetitive Ultrasonic Inspections 

 (i) Thereafter, perform a repetitive ultrasonic inspection of the rear wall of the rear half of the 

propeller hub for cracks within the compliance time specified in Table 1 of this AD. Use Appendix A 

of the applicable Dowty Mandatory Service Bulletin (MSB) listed in Table 1 of this AD. 

Inspection Reporting Requirements 

 (j) Within 10 days after each inspection, record the inspection data on a copy of Appendix B 

of the applicable MSB listed in Table 1 of this AD. Report the findings to the Manager, Boston 

Aircraft Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive 

Park, Burlington, MA 01803-5299. The Office of Management and Budget (OMB) approved the 

reporting requirements and assigned OMB control number 2120-0056. 

Alternative Methods of Compliance 

 (k) The Manager, Boston Certification Office, has the authority to approve alternative 

methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. 

Special Flight Permits 

 (l) Special flight permits may be issued in accordance with §§ 21.197 and 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where 

the requirements of this AD can be done. 
2005-20-12 3 

18 

Documents That Have Been Incorporated by Reference 

 (m) You must use the service information specified in Table 2 to perform the inspections 

required by this AD. The Director of the Federal Register approved the incorporation by reference of 

Dowty Alert Mandatory Service Bulletin (MSB) No. 61-1119, Revision 4, Dated September 14, 

2005, listed in Table 2 of this AD, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. The 

Director of the Federal Register previously approved the incorporation by reference of MSB No. 61-

1124, Revision 1, Dated October 8, 2002, and MSB No. 61-1125, Revision 1, Dated October 9, 2002, 

and MSB 61-1126, Revision 1, Dated October 9, 2002 (69 FR 34560, June 22, 2004). Contact Dowty 

Propellers, Anson Business Park, Cheltenham Road East, Gloucester GL 29QN, UK; telephone 44 

(0) 1452 716000; fax 44 (0) 1452 716001 for a copy of this service information. You may review 

copies at the FAA, New England Region, Office of the Regional Counsel, 12 New England 

Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). 

For information on the availability of this material at NARA, call 202-741-6030, or go to: 

http://www.archives.gov/federal-register/cfr/ibr-locations.html. 

TABLE 2.—INCORPORATION BY REFERENCE 

Service Bulletin No. Page Revision Date 

Alert MSB No. 61–1119 All 4 September 14, 2005. 

1 1 November 27, 2001. 

2 Original November 1, 2001. 

Appendix A 

3–6 1 November 27, 2001. 

Appendix B 1 Original November 1, 2001. 

Appendix C All Original November 27, 2001. 

Appendix D All Original December 6, 2001. 

Total pages 30 

MSB No. 61–1124 1 1 October 8, 2002. 

2–3 Original May 7, 2002. 

Appendix A All Original May 7, 2002. 

Appendix B All Original May 7, 2002. 

Appendix C All Original May 7, 2002. 

Appendix D All Original May 7, 2002. 

Total pages 30 

MSB No. 61–1125 1 1 October 9, 2002. 

2–3 Original May 7, 2002. 

Appendix A All Original May 7, 2002. 

Appendix B All Original May 7, 2002. 

Appendix C All Original May 7, 2002. 

Appendix D All Original May 7, 2002. 

Total pages 30 

MSB No. 61–1126 1 1 October 9, 2002. 

2–3 Original May 7, 2002. 

Appendix A All Original May 7, 2002. 

Appendix B All Original May 7, 2002. 

Appendix C All Original May 7, 2002. 

Appendix D All Original May 7, 2002. 

Total pages 30 
2005-20-12 4 

19 

Related Information 

 (n) United Kingdom (U.K.) Civil Aviation Authority (CAA) airworthiness directives No. G2006-0027, dated September 8, 2005; CAA UK AD No. 009-05-2002, dated April 15, 2003; CAA 

UK AD No. 010-05-2002, dated April 15, 2003; and CAA UK AD No. 011-05-2002, dated April 15, 

2003, also addresses the subject of this AD. 

 Issued in Burlington, Massachusetts, on September 26, 2005. 

Francis A. Favara, 

Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. 

[FR Doc. 05-20170 Filed 10-12-05; 8:45 am] 

BILLING CODE 4910-13-P 
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BW 2005-21 

SOCATA–GROUPE AEROSPATIALE

AIRWORTHINESS DIRECTIVE 

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 

2005-20-24 Socata–Groupe Aerospatiale: Amendment 39-14320; Docket No. FAA-2005-21464; 

Directorate Identifier 2005-CE-32-AD. 

When Does This AD Become Effective? 

 (a) This AD becomes effective on November 9, 2005. 

What Other ADs Are Affected by This Action? 

 (b) None. 

What Airplanes Are Affected by This AD? 

 (c) This AD affects the following Model TBM 700 airplanes, serial numbers 1 through 255; 

257 through 267; and 270, that are: 

 (1) equipped with a VHF1 antenna mounted under the fuselage between frame C12 and C13 

or C13 and C13bis; 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 France. The actions specified in this AD are intended to detect and 

correct cracks in the fuselage skin, which could result in loss of aircraft pressurization. Loss of 

aircraft pressurization could lead to flight crew incapacitation. 

What Must I Do To Address This Problem? 

 (e) To address this problem, you must do the following: 

 Note: The EADS SOCATA Mandatory Service Bulletin TBM Aircraft, SB 70-103, 

Amendment 1, ATA No. 53, dated September 2003, allows the pilot to perform the visual inspection 

of the fuselage skin in the VHF1 antenna mount area for cracks and loose rivets. The Federal 

Aviation Regulations (14 CFR 43.3) only allow the pilot to perform preventive maintenance as 

described in 14 CFR part 43, App. A, paragraph (c). These visual inspections are not considered 

preventive maintenance under 14 CFR part 43, App. A, paragraph (c). Therefore, an appropriatelyrated mechanic must perform all actions of this AD. 
2005-20-24 2 

21 

Actions Compliance Procedures 

(1) Inspect the 

fuselage skin in the 

VHF1 antenna 

mount area between 

frame C12 and C13 

or C13 and C13bis 

for cracks and loose 

rivets. 

Within the next 50 hours time-in-service (TIS) 

after November 9, 2005, (the effective date of this 

AD). Repetitively inspect thereafter at intervals not 

to exceed 50 hours TIS until the modification in 

paragraph (e)(2) of this AD is done. Modifying the 

VHF1 antenna bracket and interface area 

terminates the repetitive inspection requirement of 

this AD. 

Follow EADS SOCATA 

Mandatory Service Bulletin 

TBM Aircraft, SB 70–103, 

Amendment 1, ATA No. 

53, dated September 2003. 

(2) Modify the 

VHF1 antenna 

bracket and the 

antenna/fuselage 

interface. 

At whichever of the following that occurs first: 

(i) Before further flight anytime a crack or loose 

rivet is found during any inspection required in 

paragraph (e)(1) of this AD. 

(ii) Within 100 hours TIS or 12 months after 

November 9, 2005 (the effective date of this 

AD), whichever occurs later. 

Follow EADS SOCATA 

Recommended Service 

Bulletin TBM Aircraft, SB 

70–111, ATA No. 53, dated 

October 2003, and the 

applicable maintenance 

manual. 

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 Peter L. Rouse, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: 

(816) 329-4135; facsimile: (816) 329-4090. 

Is There Other Information That Relates to This Subject? 

 (g) French AD Number F-2003-367 R1, Distribution A, Issue date: February 4, 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 EADS 

SOCATA Mandatory Service Bulletin TBM Aircraft, SB 70-103, Amendment 1, ATA No. 53, dated 

September 2003, and EADS SOCATA Recommended Service Bulletin TBM Aircraft, SB 70-111, 

ATA No. 53, dated October 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 EADS SOCATA Tarbes, Direction des Services, 65921 

Tarbes Cedex 9, France; telephone: 33 (0)5 62.41.73.00; facsimile: 33 (0)5 62.41.76.54; or SOCATA 

AIRCRAFT, North Perry Airport, 7501 Pembroke Road, Pembroke Pines, Florida 33023. 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-2005-21464; Directorate 

Identifier 2005-CE-32-AD. 
2005-20-24 3 

22 

 Issued in Kansas City, Missouri, on September 28, 2005. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, Aircraft Certification Service. 

[FR Doc. 05-19930 Filed 10-11-05; 8:45 am] 

BILLING CODE 4910-13-P 
23 

BW 2005-21 

CESSNA AIRCRAFT COMPANY

AIRWORTHINESS DIRECTIVE 

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 

2005-20-25 The Cessna Aircraft Company: Amendment 39-14321; Docket No. FAA-2005-21173; 

Directorate Identifier 2005-CE-22-AD. 

When Does This AD Become Effective? 

 (a) This AD becomes effective on November 9, 2005. 

What Other ADs Are Affected By This Action? 

 (b) None. 

What Airplanes Are Affected by This AD? 

 (c) This AD affects the following airplane models and serial numbers that are: 

 (1) Equipped with an avionics bus circuit breaker switch, part number (P/N) CM3589-50, 

593-250-101, 593-250-102, W31-X2M5A-50, or W31-X1000-50; and 

 (2) certificated in any category: 

Model Serial numbers 

401 655 and 401–0001 through 401–0322. 

401A 655 and 401A0001 through 401A0132. 

401B 401B0001 through 401B0221. 

402 402–0001 through 402–0322. 

402A 402A0001 through 402A0129. 

402B 402B0001 through 402B0122, 402B0201 through 402B0249, 402B0301 through 402B0455, 

402B0501 through 402B0640, 402B0801 through 402B0935, 402B1001 through 402B1100, 

402B1201 through 402B1250, and 402B1301 through 402B1384. 

402C 689, 402C0001 through 402C0125, 402C0201 through 402C0355, 402C0401 through 

402C0528, 402C0601 through 402C0653, 402C0801 through 402C0807, and 402C0808 

through 402C1020. 

404 682, 404–0001 through 404–0136, 404–0201 through 404–0246, 404–0401 through 404–

0460, 404–0601 through 404–0695, and 404–0801 through 404–0859. 

411 642 and 411–0001 through 411–0250. 

411A 411–0251 through 411–0300. 

414 667, 414–0001 through 414–0099, 414–0151 through 414–0175, 414–0251 through 414–

0280, 414–0351 through 414–0437, 414–0451 through 414–0550, 414–0601 through 414–

0655, 414–0801 through 414–0855, and 414–0901 through 414–0965. 
2005-20-25 2 

24 

Model Serial numbers 

414A 414A0001 through 414A0121, 414A0201 through 414A0340, 414A0401 through 

414A0535, 414A0601 through 414A0680, 414A0801 through 414A0858, and 414A1001 

through 414A1212. 

421 693 and 421–0001 through 421–0200. 

421A 421A0001 through 421A0158. 

421B 421B0001 through 421B0056, 421B0101 through 421B0147, 421B0201 through 421B0275, 

421B0301 through 421B0486, 421B0501 through 421B0665, and 421B0801 through 

421B0970. 

421C 421C0001 through 421C0171, 421C0201 through 421C0350, 421C0401 through 421C0525, 

421C0601 through 421C0715, 421C0801 through 421C0910, 421C1001 through 421C1115, 

421C1201 through 421C1257, 421C1401 through 421C1413, and 421C1801 through 

421C1807. 

425 425–0001 through 425–0236. 

441 698 and 441–0001 through 441–0362. 

What is the Unsafe Condition Presented in This AD? 

 (d) This AD is the result of reports of smoke and a burning smell in the cockpit. The actions 

specified in this AD are intended to prevent failure of the avionics bus circuit breaker switch, which 

could result in smoke and a burning smell in the cockpit. This failure could lead to reduced ability to 

control the airplane. 

What Must I do to Address This Problem? 

 (e) To address this problem, you must do the following: 

Actions Compliance Procedures 

(1) Inspect the avionics bus circuit 

breaker switch to determine the part 

number (P/N) and date code. (i) If 

the P/N is CM3589–50, 593–250–

101, 593–250–102, W31–X2M5A–

50, or W31–X1000–50; and (ii) The 

date code is 0434 or later; then (iii) 

No further action is required. 

Within the next 200 

hours time-in-service 

(TIS), the next 12 

months, or at the next 

scheduled inspection, 

after November 9, 

2005 (the effective 

date of this AD), 

whichever occurs 

first. 

For Models 425 and 441 airplanes, 

follow the procedures in Cessna 

Conquest Service Bulletin CQB05–2, 

dated February 21, 2005, and the 

applicable maintenance manual. For all 

other affected airplane models, follow 

the procedures in Cessna Multi-engine 

Service Bulletin MEB05–1 dated 

February 21, 2005, and the applicable 

maintenance manual. 

(2) If the P/N is CM3589–50, 593–

250–101, 593–250–102, W31–

X2M5A–50, or W31–X1000–50 

and there is no date code, replace 

the avionics bus circuit breaker 

switch with a P/N CM3589–50 that 

has a date code of 0434 or later. 

Before further flight 

after the inspection 

required in paragraph 

(e)(1) of this AD. 

For Models 425 and 441 airplanes, 

follow the procedures in Cessna 

Conquest Service Bulletin CQB05–2, 

dated February 21, 2005, and the 

applicable maintenance manual. For all 

other affected airplane models, follow 

the procedures in Cessna Multi-engine 

Service Bulletin MEB05–1, dated 

February 21, 2005, and the applicable 

maintenance manual. 
2005-20-25 3 

25 

Actions Compliance Procedures 

(3) If the P/N is CM3589–50, 593–

250–101, 593–250–102, W31–

X2M5A–50, or W31–X1000–50, or 

W31–X1000–50 and the date code 

is earlier than 0434, the part has a 

safe life limit of 1,000 hours TIS 

and must be replaced within the 

1,000-hour time limit with a P/N 

CM3589–50 that has a date code of 

0434 or later. 

Within the 1,000-

hour TIS safe life 

limit 

For Models 425 and 441 airplanes, 

follow the procedures in Cessna 

Conquest Service Bulletin CQB05–2, 

dated February 21, 2005, and the 

applicable maintenance manual. For all 

other affected airplane models, follow 

the procedures in Cessna Multi-engine 

Service Bulletin MEB05–1, dated 

February 21, 2005, and the applicable 

maintenance manual. 

(4) Do not install a P/N CM3589–

50, 593–250–101, 593–250–102, 

W31–X2M5A–50, or W31–X1000–

50 that does not have a date code or 

has a date code earlier than 0434. 

As of November 9, 

2005 (the effective 

date of this AD). 

Not applicable. 

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, Wichita Aircraft Certification Office (ACO), FAA. For information on any 

already approved alternative methods of compliance, contact Gerald Pilj, Aerospace Engineer, FAA 

Wichita ACO, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 

946-4151; facsimile: (316) 946-4107. 

Does This AD Incorporate Any Material by Reference? 

 (g) You must do the actions required by this AD following the instructions in Cessna 

Conquest Service Bulletin CQB05-2, dated February 21, 2005, and Cessna Multi-engine Service 

Bulletin MEB05-1, dated February 21, 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 The Cessna Aircraft Company, Citation 

Marketing Division, Product Support P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-

5800; facsimile: (316) 942-9006. 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-2005-21173; Directorate 

Identifier 2005-CE-22-AD. 

 Issued in Kansas City, Missouri, on September 28, 2005. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, Aircraft Certification Service. 

[FR Doc. 05-19928 Filed 10-11-05; 8:45 am] 

BILLING CODE 4910-13-P 
26 

BW 2005-21 

AVIOINTERIORS S.P.A.

AIRWORTHINESS DIRECTIVE 

APPLIANCE 

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 

CORRECTION: There is a typo in the AD number reference in the Federal Register (FR), page 

59243, 3rd column, October 12, 2005 of this AD. The correct AD number should read "2005-20-26". 

We've corrected this copy and will issue a correction to the FR. 

2005-20-26 Aviointeriors S.p.A. (formerly ALVEN): Amendment 39-14323. Docket No. FAA2005-20848; Directorate Identifier 2005-NE-02-AD. 

Effective Date 

 (a) This airworthiness directive (AD) becomes effective November 16, 2005. 

Affected ADs 

 (b) None. 

Applicability 

 (c) This AD applies to Aviointeriors S.p.A. (formerly ALVEN), series 312 box mounted 

seats, part number (P/N) 312( )( )27-( )( )( ) ( )( ) and P/N 312( )( )36-( )( )( )( )( ). These seats are 

installed in, but not limited to, Fokker Model F27 Mark 050, Mark 500, and Mark 600 airplanes. 

 (d) The parentheses appearing in the seat P/N indicate the presence or absence of an 

additional letter(s), or number(s), that varies the basic seat configuration. This AD still applies 

regardless of whether these letters, or numbers, are present or absent in the seat P/N designation. 

Unsafe Condition 

 (e) This AD results from 10 reports of cracked attachments of 

series 312 box mounted seats. We are issuing this AD to prevent series 312 box mounted seats from 

detaching from the passenger compartment floor, which could result in injury to the occupant of the 

seat, and prevent evacuation of passengers in the event of an emergency. 

Compliance 

 (f) You are responsible for having the actions required by this AD performed within the 

compliance times specified unless the actions have already been done. 

Attachments That Have Already Accumulated 8,000 Hours Time-In-Service (TIS) or More 

 (g) For attachments that have already accumulated 8,000 hours TIS or more on the effective 

date of this AD, do the following: 
2005-20-26 2 

27 

 (1) Within 90 days after the effective date of this AD, replace attachments with new 

attachments of the same P/N, using Section 2., Replacement Procedure, Steps 2.4 though 2.6 of 

Aviointeriors Service Bulletin No. 312/912-05, Revision 1, dated August 24, 2001. 

 (2) Perform repetitive visual inspections as specified in paragraph (i) of this AD. 

Initial Visual Inspection 

 (h) Perform an initial visual inspection of the seat outboard and inboard attachments for 

cracks, within 90 days after the effective date of this AD, as follows: 

 (1) Inspect seat outboard attachment, part number (P/N) DM03313-1, and seat inboard 

attachment, P/N DM03314-1, using Section 2., Inspection Procedure, Steps 2.1 through 2.5 of 

Aviointeriors Service Bulletin (SB) No. 312/912-05, Revision 1, dated August 24, 2001. 

 (2) Replace any cracked attachment with a new attachment of the same P/N, using Section 2., 

Replacement Procedure, Steps 2.4 though 2.6 of Aviointeriors SB No. 312/912-05, Revision 1, dated 

August 24, 2001. 

 (3) Replace attachments when they have accumulated 8,000 hours time-in-service (TIS), with 

new attachments of the same P/N, using Section 2., Replacement Procedure, Steps 2.4 though 2.6 of 

Aviointeriors SB No. 312/912-05, Revision 1, dated August 24, 2001. 

Repetitive Visual Inspections 

 (i) Within 650 hours TIS after the last inspection, or within 650 hours TIS after attachment 

was replaced, and whenever the seat is being installed or removed, perform repetitive visual 

inspections for cracks, and replace cracked seat outboard and inboard attachments. Use paragraphs 

(h)(1) through (h)(3) of this AD to inspect and disposition the attachments. 

Alternative Methods of Compliance 

 (j) The Manager, Boston Aircraft Certification Office, has the authority to approve alternative 

methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. 

Related Information 

 (k) Ente Nazionale per l'Aviazione Civile airworthiness directive AD 2001-479, dated 

November 12, 2001, also addresses the subject of this AD. 

Material Incorporated by Reference 

 (l) You must use Aviointeriors Service Bulletin No. 312/912-05, Revision 1, dated August 24, 

2001, to perform the actions required by this AD. 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. Contact Aviointeriors S.p.A., Via Appia Km. 66.4–04013 Latina, Italy; telephone: 39-0773-6891; 

fax: 39-0773-631546, for a copy of this service information. You may review copies at the Docket 

Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, 

Room PL-401, Washington, DC 20590-0001, on the internet at http://dms.dot.gov, or at the National 

Archives and Records Administration (NARA). For information on the availability of this material at 

NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. 
2005-20-26 3 

28 

 Issued in Burlington, Massachusetts, on September 30, 2005. 

Francis A. Favara, 

Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. 

[FR Doc. 05-19941 Filed 10-11-05; 8:45 am] 

BILLING CODE 4910-13-P 
29 

BW 2005-21 

BELL HELICOPTER TEXTRON

AIRWORTHINESS DIRECTIVE 

ROTORCRAFT 

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 

2005-20-38 Bell Helicopter Textron: Amendment 39-14335. Docket No. FAA-2005-22634; 

Directorate Identifier 2005-SW-12-AD. 

Applicability 

 Model 212, 412, and 412EP helicopters modified with Aeronautical Accessories, Inc. (AAI), 

Supplemental Type Certificate (STC) SH2820SO; or with AAI Parts Manufacturer Approval (PMA) 

reservoir assembly, part number (P/N) 212-372-050; or with adapter, P/N 212-371-002, installed, 

certificated in any category. 

Compliance 

 Required as indicated, unless accomplished previously. 

 To prevent rupture of an adapter, uncontrolled jetting of pressurized gas from the nitrogen 

bottle, and subsequent injury to occupants or damage to the helicopter, accomplish the following: 

 (a) Within the next 24 hours time-in-service (TIS) or before the next emergency floatation 

supply bottle nitrogen charging, whichever occurs first, do the following: 

 (1) Vent the nitrogen from the reservoir assembly by following the Accomplishment 

Instructions, Part II–Floatation System Discharging, of AAI Alert Service Bulletin ASB No. AA05005, Revision A, dated June 27, 2005 (ASB). 

 (2) Remove the valve assembly and air line from the adapter, and inspect the counter bore 

depth (dimension D) as shown in Figure 1 of the ASB. 

 (i) If dimension D, as depicted in Figure 1 of the ASB, does not exceed .860 inch, recharge 

the floatation system by following the Accomplishment Instructions, Part III–Floatation System 

Charging, and referring to Figures 2 and 3 of the ASB. 

 (ii) If dimension D, as depicted in Figure 1 of the ASB, exceeds .860 inch, replace the 

reservoir assembly and the adapter with airworthy parts before further flight. 

 (b) 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 Rotorcraft Certification Office, FAA, for 

information about previously approved alternative methods of compliance. 

 (c) Discharging and recharging the floatation system and inspecting the counter bore depth 

dimension of the adapter shall be done in accordance with the specified portions of Aeronautical 

Accessories, Inc. Alert Service Bulletin No. AA-05005, Revision A, dated June 27, 2005. The 
2005-20-38 2 

30 

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 Aeronautical Accessories, Inc., P. O. Box 

3689, Bristol, Tennessee 37625-3689. Copies may be inspected at the National Archives and Records 

Administration (NARA). For information on the availability of this material at NARA, call 202-741-

6030, or go to: 

http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. 

 (d) This amendment becomes effective on October 28, 2005. 

 Issued in Fort Worth, Texas, on September 30, 2005. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. 

[FR Doc. 05-20324 Filed 10-12-05; 8:45 am] 

BILLING CODE 4910-13-P