FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2005-05 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

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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; Biweekly 2005-01 2004-26-09

2004-26-11 2005-01-04

2005-01-10 2005-01-11

Rolls-Royce Corporation

S 98-15-13

S 74-06-01

Bell Helicopter Textron Canada Raytheon Aircraft Company

The New Piper Aircraft, Inc Pilatus Aircraft Ltd.

Engine: 250-B17, -B17B, -B17C, -B17D, -B17E, 250-C20, -C20B, -C20F, -C20J, -C20S, and -C20W Series Turboprop and Turboshaft Rotorcraft: 222, 222B, 222U, 230, 430 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 PA-23-235, PA-23-250, and PA-E23-250 PC-12 and PC-12/45

Biweekly 2005-02 98-20-38 R1

R

Raytheon Aircraft Company

2005-01-14 2005-01-17 2005-01-18

S 2002-21-16 S 98-03-14 S 93-25-07

Bombardier-Rotax GmbH EXTRA Flugzeugbau GmbH Raytheon Aircraft Company

2005-01-19

S 2004-10-15

GARMIN International Inc

2005-02-01

The Lancair 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 Engine: 912 F, 912 S, and 914 F Series Reciprocating EA–300 and EA–300/S 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 Appliance: GTX 33, GTX 33D, GTX 330, and GTX 330D Mode S Transponders LC40–550FG and LC42–550FG

Biweekly 2005-03 2005-01-04

COR S 98-15-13

Raytheon Aircraft Company

2005-01-18

COR S 93-25-07

Raytheon Aircraft Company

2005-02-11 2005-03-04

COR

Gippsland Aeronautics Pty. Ltd. Pacific Aerospace Corp., Ltd.

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 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 GA8 750XL

Biweekly 2005-04 2005-01-04

COR S 98-15-13

2005-03-07 2005-03-08 2005-03-09

2005-03-10 2005-04-09

Raytheon Aircraft Company

Bell Helicopter Textron Canada Eurocopter France Eurocopter France

S 2002-08-54 S 2004-26-11

Bell Helicopter Textron Bell Helicopter Textron Canada

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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 Rotorcraft: 407 Rotorcraft: AS350B, BA, B1, B2, B3, C, D, D1, and EC130 B4 Rotorcraft: EC 155B, EC155B1, SA-360C, SA-365C, SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1 Rotorcraft: 222, 222B, 222U, and 230 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; Biweekly 2005-05 2005-04-08 2005-04-10 2005-04-16 2005-05-51 2005-05-52 2005-05-53 2005-05-53 R1

Hartzell Propeller Inc. General Electric Company

E E, S 2005-05-51 E E, R, S 2005-0553

Propeller: HC-B3TN-5( )/T10282( ) Engine: CT58-140-1, CT58-140-2, and surplus military T58-GE-5, -10, -100, and ''402 turboshaft PC-12 and PC-12/45 402C and 414A 402C and 414A 172R, 172S, 182T, and T182T 172R, 172S, 182T, and T182T

Pilatus Aircraft Ltd. Cessna Aircraft Company Cessna Aircraft Company Cessna Aircraft Company Cessna Aircraft Company

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BW 2005-05 HARTZELL PROPELLER INC. AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-04-08 Hartzell Propeller Inc.: Amendment 39-13980. Docket No. 2003-NE-50-AD. Effective Date (a) This AD becomes effective March 29, 2005. Affected ADs (b) This AD supersedes Priority Letter AD 88-24-15. Applicability (c) This AD applies to Hartzell Propeller Inc. model HC-B3TN-5( )/T10282( ) propellers installed on the airplane and engine combinations shown in the following Table 1 (excluding propellers with blades part number (P/N) T10282N( ), T10282NB( ), T10282NK( ), or T10282NE( ) installed).

Airplane model Fairchild SA226–TC Fairchild SA226–AT Fairchild SA226–T

TABLE 1.—APPLICABILITY Propeller model Engine model HC–B3TN–5( )/T10282( ) Garrett TPE331–10UA–511G

(d) For reference, airplanes incorporating Supplemental Type Certificates (STCs) SA344GLD, SA4872SW, and SA345GL-D have these engine, propeller, and airplane combinations. (e) The parentheses appearing in the propeller model number indicates the presence or absence of an additional letter(s) that varies the basic propeller model. This AD still applies regardless of whether these letters are present or absent in the propeller model designation. Unsafe Condition (f) This AD results from a review of all currently effective ADs. That review determined that Priority Letter AD 88-24-15 was not published in the Federal Register to make it effective to all operators, as opposed to just the operators who received actual notice of the original Priority Letter AD. This AD also results from the discovery that the original AD omitted an airplane model with a certain STC from the applicability. We are issuing this AD to prevent possible blade failure near the

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2005-04-08 2

hub which can result in blade separation, engine separation, damage to the airplane, and possible loss of the airplane. Compliance (g) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Required Actions (h) Within 10 hours time-in-service (TIS) after the effective date of this AD, perform a document search to determine if the following actions have been done: (1) The propeller blades meet the initial and repetitive compliance requirements of Priority Letter AD 88-24-15. (2) The P/N T10282( ) propeller blades have been replaced with P/N T10282N( ), T10282NB( ), T10282NK( ), or T10282NE( ) propeller blades. (i) If the actions in paragraph (h)(1) or (h)(2) of this AD have not been done, then do one of the following: (1) Inspect the blades using Paragraph 3 of the Accomplishment Instructions of Hartzell Service Bulletin (SB) No. 136, Revision Letter ''I,'' dated April 25, 2003, within 500 hours timesince-new (TSN) or time-since-last-overhaul (TSLO) and not to exceed two years after the effective date of this AD, whichever occurs first; and thereafter within 500 service-hour intervals; or (2) Replace with P/N T10282N( ), T10282NB( ), T10282NK( ), or T10282NE( ) propeller blades as applicable, within 500 hours TSN or TSLO and not to exceed two years after the effective date of this AD, whichever occurs first. (j) If the actions in paragraph (h)(1) of this AD have been done, but not the actions in paragraph (h)(2) of this AD, then do the following: (1) Inspect the blades within 500 hours since the last Hartzell SB No. 136E, or later Revision, inspection, and thereafter within 500 service hour intervals, using Paragraph 3 of the Accomplishment Instructions of Hartzell SB No. 136, Revision Letter ''I,'' dated April 25, 2003. (2) Replace before further flight all blades showing evidence of cracks or other unairworthy conditions, as noted in Hartzell SB No. 136, Revision Letter ''I,'' dated April 25, 2003, with airworthy blades. Hartzell SB No. 136 (k) Since Hartzell SB No. 136E was issued, the SB has been revised to 136F, 136G, 136H, and 136I. Any of these revisions are suitable for determining past compliance, as they are all approved as alternative methods of compliance (AMOC). After the effective date of this AD, compliance is restricted to SB No. 136, Revision Letter ''I,'' or later versions when approved by an AMOC. Optional Terminating Action (l) Installation of propeller blades, P/N T10282N( ), T10282NB( ), T10282NK( ), or T10282NE( ) as applicable, onto a Hartzell Propeller Inc. model HC-B3TN-5( ) propeller constitutes 6

2005-04-08 3

terminating action to the inspections, repairs, and replacements specified in paragraphs (i) through (j)(2) of this AD. Alternative Methods of Compliance (m) The Manager, Chicago Aircraft Certification Office, has the authority to approve alternate methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Material Incorporated by Reference (n) You must use Hartzell SB No. 136 (HC-SB-61-136), Revison Letter ''I,'' dated April 25, 2003, to perform the inspections 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. You can get a copy from Hartzell Propeller Inc. Technical Publications Department, One Propeller Place, Piqua, OH 45356; telephone (937) 778-4200; fax (937) 778-4391. You can 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/code_of_federal_regulations/ibr_locations.html. Related Information (o) None. Issued in Burlington, Massachusetts, on February 11, 2005. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-3046 Filed 2-18-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-05 GENERAL ELECTRIC COMPANY AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS

2005-04-10 General Electric Company: Amendment 39-13982. Docket No. 2003-NE-59-AD. Effective Date (a) This airworthiness directive (AD) becomes effective March 29, 2005. Affected ADs (b) None. Applicability (c) This AD applies to General Electric Company (GE) CT58-140-1, CT58-140-2, and surplus military T58-GE-5, -10, -100, and ''402 turboshaft engines with stage 1 compressor disks, part number (P/N) 5001T20P01, that have a serial number (SN) listed in the following Table 1:

GATD0PD2 GATD0PD3 GATD0PD5 GATD0PD6 GATD0PD7 GATD0PD8 GATD0PD9 GATD0PDA GATD0PDC GATH53GC GATH53GD GATH53GE GATH53GF GATH53GH GATH53GJ GATH53GK GATH5T70 GATH5T71 GATH5T72 GATH5T73 GATH5T74 GATH5T75

GATH5T76 GATH5T77 GATH5T78 GATH5T79 GATH5T7A GATH5T7C GATH5T7D GATH5T7E GATH5T7F GATH5T7G GATH5T7H GATH6CDL GATH6CDM GATH6CDN GATH6CDP GATH6CDR GATH6CDT GATH6CE0 GATH6CE1 GATH6CE2 GATH6CE3 GATH6CE4

GATH6CE5 GATH6CE6 GATH6CE7 GATH6CE8 GATH6CE9 GATH6CEA GATH6CEC GATH6CED GATH6CEE GATH6CEF GATH6RH8 GATH6RH9 GATH6RHC GATH6RHD GATH6RHE GATH6RHF GATH6RHG GATH6RHH GATH6RHJ GATH6RWT GATH6RWW GATH6T00

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GATH6T01 GATH6T02 GATH6T03 GATH6T04 GATH6T05 GATH7K4K GATH7K4L GATH7K4M GATH7K4N GATH7K4P GATH7K4R GATH7K4T GATH7K5G GATH7KGH GATH7KGK GATH7KGL GATH7KGM GATH7KGN GATH7KGP GATH7KGR GATH7KGT GATH7KGW

GATH7KH0 GATH7KH1 GATH7KH2 GATH7LAL GATH7LAM GATH7LAN GATH7LAP GATH7LAR GATH7LAT GATH7LAW GATH7LC0 GATH7LC1 GATH7LC2 GATH7LC3 GATH7LC4 GATH7LC5 GATH7LC6 GATH7LC7 GATH7LC8 GATH7M8G GATH7M8H GATH7M8J

2005-04-10 2

GATH7M8K GATH7M8L GATH7M8M GATH7M8N GATH7MLK GATH7MLL GATH7MLM GATH7MLN GATH7MLP GATH7MLR GATH7MLT GATH7MLW GATH7MM0 GATH7MM1 GATH7MM2 GATH7MM3 GATH7PPT GATH7PPW GATH7PR0 GATH7PR1 GATH7PR2 GATH7PR3 GATH7PR4 GATH7PR5 GATH7PR6 GATH7PR7 GATH7PR8 GATH7PR9 GATH7PRA GATH7PRC GATH7PRD GATH7PRE GATH7PRF GATH7PRG GATH7PRH GATH7PRJ GATH7PRK GATH7PRL GATH7PRM GATH7PRN GATH7PRP GATH7PRR

GATH7PRT GATH7PRW GATH7PT0 GATH7RTP GATH7RTR GATH7RTT GATH82R8 GATH82R9 GATH82RA GATH82RD GATH82RE GATH82RF GATH82RG GATH82RH GATH82RJ GATH82RK GATH82RL GATH82RM GATH82RN GATH82RP GATH82RR GATH82RT GATH82RW GATH82T0 GATH82T1 GATH86JD GATH86JE GATH86JF GATH86JG GATH86JH GATH86JJ GATH86JK GATH86JL GATH86JM GATH86JN GATH86JP GATH86JR GATH86JT GATH86JW GATH86K0 GATH86K2 GATH86K3

GATH86K4 GATH86K5 GATH8A5G GATH8A5H GATH8A5J GATH8A5K GATH8A5L GATH8A5M GATH8A5N GATH8A5P GATH8A5T GATH8A5W GATH8A60 GATH8A61 GATH8A62 GATH8A63 GATH8A64 GATH8A66 GATH8A67 GATH8A68 GATH8GRG GATH8GRH GATH8GRK GATH8GRL GATH8GRM GATH8GRN GATH8GRP GATH8GRR GATH8GRT GATH8GRW GATH8GT0 GATH8GT1 GATH8GT3 GATH8GT5 GATH8GT7 GATH8GT8 GATH8HGF GATH8HGG GATH8HGH GATH8HGJ GATH8HGK GATH8HGL

GATH8HGM GATH8HGN GATH8HGP GATH8HGR GATH8HGT GATH8HGW GATH8HH0 GATH8HH1 GATH8HH2 GATH8HH3 GATH8HH4 GATH8HH5 GATH8HH6 GATH8HH7 GATH8K0H GATH8K0J GATH8K0K GATH8K0L GATH8K0M GATH8K0N GATH8K0P GATH8K0R GATH8K0T GATH8K0W GATH8K12 GATH8K13 GATH8K14 GATH8K15 GATH8K16 GATH8K17 GATH8K18 GATH8K19 GATH8W7H GATH8W7J GATH8W7L GATH8W7M GATH8W7N GATH8W7P GATH8W7R GATH8W7T GATH8WD4 GATH8WD5

GATH8WD6 GATH8WD7 GATH8WD8 GATH8WD9 GATH8WDA GATH8WDC GATH8WDD GATH8WDE GATH8WDF GATH8WDG GATH8WDH GATH8WDJ GATH8WDK GATH8WDL GATH94R3 GATH94R4 GATH94R6 GATH94R7 GATH94R8 GATH94R9 GATH94RA GATH94RC GATH94RD GATH94RE GATH94RF GATH94RG GATH94RJ GATH94RK GATH94RN GATH94RP GATH94RR GATH94RT GATH96HF GATH96HG GATH96HK GATH96HL GATH96HM GATH96HN GATH96HR GATH96HT GATH96HW GATH96J0

These engines are installed on, but not limited to, Agusta S.p.A AS-61N, AS-61N1, Sikorsky S-61L, S-61N, S-61R, and S-61NM helicopters, and the following surplus military helicopters that have been certified in accordance with sections 21.25 or 21.27 of the Federal Aviation Regulations (14 CFR 21.25 or 21.27): Sikorsky S-61D and S-61V, Glacier CH-3E, Siller CH-3E and SH-3A, and Robinson Crane CH-3C, CH-3E, HH-3C, HH-3E, and Carson S-61L helicopters.

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2005-04-10 3

Unsafe Condition (d) This AD results from two reports of low blade tip clearances in the compressor. We are issuing this AD to prevent low-cycle-fatigue (LCF) cracking and failure of the stage 1 compressor disk, an uncontained engine failure, and damage to the helicopter. 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. Replacement of Stage 1 Compressor Disks (f) If you have a stage 1 compressor disk, P/N 5001T20P01, with a SN listed in Table 1 of this AD, replace that stage 1 compressor disk at or before reaching a reduced LCF life limit for those affected disks of 2,100 hours time-since-new (TSN) or by December 31, 2008, whichever occurs first. GE Alert Service Bulletin (ASB) No. CT58 S/B 72-A0196, dated July 24, 2003, contains information on replacing the stage 1 compressor disk. (g) After the effective date of this AD, do not install any stage 1 compressor disk, P/N 5001T20P01, that has a SN listed in Table 1 of this AD and has 2,100 hours TSN or more, into any engine. Alternative Methods of Compliance (h) The Manager, Engine 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. Material Incorporated by Reference (i) None. Related Information (j) GE Alert Service Bulletin No. CT58 S/B 72-A0196, dated July 24, 2003, pertains to the subject of this AD. Issued in Burlington, Massachusetts, on February 10, 2005. Francis A. Favara, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-3190 Filed 2-18-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-05 PILATUS AIRCRAFT LTD. AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-04-16 Pilatus Aircraft Ltd.: Amendment 39-13988; Docket No. FAA-05-20399; Directorate Identifier 2005-CE-02-AD. When Does This AD Become Effective? (a) This AD becomes effective on March 8, 2005. Are Any Other ADs Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects airplane Models PC-12 and PC-12/45 airplanes with serial numbers 322 through 400 that are 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. We are issuing this AD to detect and replace windshield de-ice wiring of the incorrect size, which could result in heat damage of the windshield de-ice wiring. This failure could lead to possible fire in the overhead panel of the flight compartment. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions (1) Inspect the windshield de-ice wiring on both the left and right side windshields for heat damage of the wires, splices, and related link wires in the area of the terminal block 152

Compliance Within 10 hours time-in-service (TIS) or 30 days, whichever occurs first, after March 8, 2005 (the effective date of this AD). This is a one-time inspection.

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Procedures Follow Pilatus Aircraft Ltd. Service Bulletin No. 30–009, dated January 25, 2005.

2005-04-16 2

(2) Inspect the windshield deice wiring and related link wires on both the left and right side windshields to verify that wires of the correct size (American Wire Gage) are installed as specified in Service Bulletin 30– 009, dated January 25, 2005. (3) If any heat damage or incorrect wiring is found, replace the damaged or incorrect wires.

Within 10 hours TIS or 30 days, Follow Pilatus Aircraft Ltd. Service Bulletin No. 30–009, whichever occurs first, after March 8, 2005 (the effective date dated January 25, 2005. of this AD). This is a one-time in-spection.

Before further flight

Follow Pilatus Aircraft Ltd. Service Bulletin No. 30–009, dated January 25, 2005.

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 L. Rudolph, Aerospace Engineer, ACE-112, 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) FOCA Airworthiness Directive HB-2005-079, dated February 11, 2005, 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 Aircraft Ltd. Service Bulletin No. 30-009, dated January 25, 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. You may get a copy from Pilatus Aircraft Ltd., CH-6371 Stans, Switzerland. To get a copy of this service information, contact Doug Rudolph, Aerospace Engineer, ACE-112, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 3294059; facsimile: (816) 329-4090. 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 20590001 or on the Internet at http://dms.dot.gov. The docket number is Docket No. FAA-05-20399; Directorate Identifier 2005-CE-02-AD. Issued in Kansas City, Missouri, on February 17, 2005. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-3634 Filed 2-28-05; 8:45 am] BILLING CODE 4910-13-P 12

BW 2005-05 THE CESSNA AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS

2005-05-51 THE CESSNA AIRCRAFT COMPANY: Directorate Identifier 2005-CE-06-AD. When Does This AD Become Effective? (a) This emergency AD becomes effective upon receipt. Are Any Other ADs Affected By This Action? (b) This AD supersedes AD 2000-23-01, Amendment 39-11971 (65 FR 70645). What Airplanes Are Affected by This AD? (c) This AD affects Model 402C and 414A airplanes, all serial numbers, that: (1) are certificated in any category; and (2) do not incorporate a spar strap modification on each wing spar following Cessna Service Bulletin MEB02-5, dated June 24, 2002, and Cessna Service Kit SK402-47, dated June 24, 2002. What is the Unsafe Condition Presented in This AD? (d) This AD is the result of extensive cracks found in the wing spars of two of the affected airplanes. We are issuing this AD to detect and correct cracking in the wing spars before the cracks grow to failure. Such wing failure could result in the wing separating from the airplane with consequent loss of control of the airplane What Must I do to Address This Problem? (e) Inspections: Perform both an external and internal inspection of the forward, aft, and auxiliary wing spars for cracks at the times below that are applicable (pay particular attention to the areas specified in paragraph (f) of this AD). Do these inspections following the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Service Bulletin MEB99-3, dated May 6, 1999 (Model 402C); or Cessna Service Bulletin MEB00-7, dated June 24, 2002 (Model 414A): Affected Airplanes (1) For all Model 402C airplanes with fewer than 15,000 hours total time-inservice (TIS).

Initial Inspection Upon accumulating 10,000 hours TIS on the airplane or at the next inspection that would have been required by AD 200023-01, whichever occurs later. 13

Repetitive Interval Thereafter at intervals not to exceed 110 hours until accumulating 15,000 hours TIS.

2005-05-51 2

(2) For all Model 414A airplanes, serial numbers 414A0001 through 414A0047 and 414A0049 through 414A0200.

(3) For the following airplanes that have 15,000 hours or more TIS or upon accumulating 15,000 hours TIS: (i) All Model 402C airplanes. (ii) Model 414A airplanes, serial numbers 414A0201 through 414A1212.

Upon accumulating 8,500 hours TIS on the airplane or prior to further flight after receipt of this AD, whichever occurs later. To return/position the airplane to a home base, hangar, maintenance facility, etc., you may operate the airplane up to 3 hours TIS provided the flight(s) occur(s) no later than 30 days after receipt of this emergency AD. Only the PILOT AND ANY ADDITIONAL FLIGHT CREW MEMBER REQUIRED FOR SAFE OPERATION is allowed for this flight; and FLIGHT INTO KNOWN OR FORECAST MODERATE OR SEVERE TURBULENCE IS PROHIBITED. Prior to further flight after receipt of this AD. To return/position the airplane to a home base, hangar, maintenance facility, etc., you may operate the airplane up to 3 hours TIS provided the flight(s) occur(s) no later than 30 days after receipt of this emergency AD. Only the PILOT AND ANY ADDITIONAL FLIGHT CREW MEMBER REQUIRED FOR SAFE OPERATION is allowed for this flight; and FLIGHT INTO KNOWN OR FORECAST MODERATE OR SEVERE TURBULENCE IS PROHIBITED.

Thereafter at intervals not to exceed 15 hours TIS.

Thereafter at intervals not to exceed 15 hours TIS.

(f) Specific Inspection Areas of Emphasis: When doing the inspections, pay particular attention to the following areas: (1) Just Outboard of the Engine Beam (i) The lower spar cap at Wing Station (WS) 114. (ii) The three rivets on both the inboard and outboard sides of WS 114 (total of six rivets) in the lower spar cap as viewed from the access hole. (iii) The spar web at WS 112.5. (2) Just Inboard of the Inboard Engine Beam (i) The lower spar cap between WS 80 and WS 89. (ii) The two attach bolts just inboard of the WS 89.18 rib. (g) Cracks found: If you find any crack on any forward, aft, or auxiliary wing spar; or in surrounding structure such as spar webs or skins during any inspection required by this AD, prior to further flight do the following: 14

2005-05-51 3

(1) Obtain an FAA-approved repair scheme from the Cessna Aircraft Company, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 941-7550, facsimile: (316) 942-9008; and (2) Incorporate this repair scheme. (h) Reporting Requirement: As soon as possible, but no later than 24 hours after any inspection required by this AD: (1) Submit a report of inspection findings to the Manager, Wichita Aircraft Certification Office (ACO), by fax: (316) 946-4107. (i) Include a report for “cracks found” or “no cracks found” on the initial inspection; and (ii) Include a report only for “cracks found” on the repetitive inspections. (2) The report must include your name and a contact phone number, the results of the findings, a description of any cracking found, the airplane serial number, and the total number of hours TIS on the airplane. The “Lower Wing Spars and Skin Inspection Report” included as page 6 of Cessna Service Bulletin MEB99-3, dated May 6, 1999, may be utilized for this reporting requirement. May I Request an Alternative Method of Compliance? (i) 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, FAA. For information on any already approved alternative methods of compliance or for further information about this AD, contact Paul Nguyen, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, MidContinent Airport, Wichita, Kansas 67209; telephone: (316) 946-4125; facsimile: (316) 946-4107; email: [email protected]. May I Get Copies of the Documents Referenced in this AD? (j)You may get copies of the documents referenced in this AD Cessna Aircraft Company, Product Support P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-5800; facsimile: (316) 942-9006. Issued in Kansas City, Missouri, on February 20, 2005.

David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.

15

BW 2005-05 THE CESSNA AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS

2005-05-52 THE CESSNA AIRCRAFT COMPANY: Directorate Identifier 2005-CE-07-AD. When Does This AD Become Effective? (a) This emergency AD becomes effective upon receipt. Are Any Other ADs Affected By This Action? (b) This AD supersedes emergency AD 2005-05-51, which superseded AD 2000-23-01. What Airplanes Are Affected by This AD? (c) This AD affects Model 402C and 414A airplanes, all serial numbers, that: (3) are certificated in any category; and (2) do not incorporate a spar strap modification on each wing spar following the original release of (or a later FAA-approved revision to) Cessna Service Bulletin MEB02-5 and Cessna Service Kit SK402-47 (currently at MEB02-5 Revision 2 and SK402-47B). What is the Unsafe Condition Presented in This AD? (d) This AD is the result of extensive cracks found on three wing spars of the affected airplanes. We are issuing this AD to detect and correct cracking in the wing spars before the cracks grow to failure. Such a wing failure could result in the wing separating from the airplane with consequent loss of control of the airplane. What Must I do to Address This Problem? (e) Visual Inspections for all Model 402C airplanes With Fewer than 15,000 Hours Total Time-in-service (TIS): Initially inspect upon accumulating 10,000 hours TIS on the airplane or at the next inspection that would have been required by AD 2000-23-01 or emergency AD 2005-05-51, whichever occurs later. Repetitively inspect thereafter at intervals not to exceed 110 hours TIS until accumulating 15,000 hours TIS: (1) Perform both a visual external and internal inspection of the forward, aft, and auxiliary wing spars for cracks. (2) Do these visual inspections following the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Service Bulletin MEB99-3 (Model 402C), Revision 2, dated February 28, 2005. 16

2005-05-52 2

(3) When doing the inspections, pay particular attention to the following areas: (i) Just Outboard of the Engine Beam (A) The main lower spar cap at Wing Station (WS) 114. (B) The three rivets on both the inboard and outboard sides of WS 114 (total of six rivets) in the main lower spar cap as viewed from the access hole. (C) The main spar web at WS 112.5. (ii) Just Inboard of the Inboard Engine Beam (A) The main lower spar cap between WS 80 and WS 89. (B) The two attach bolts on the main spar just inboard of the WS 89.18 rib. (f) Eddy Current and Visual Inspections: Perform eddy current inspections of the forward wing spars combined with visual inspections of the aft and auxiliary spars. Do these inspections following the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Service Bulletin MEB99-3 (Model 402C) or Cessna Service Bulletin MEB00-7 (Model 414A) both at Revision 2 and both dated February 28, 2005. Affected Eddy Current and Visual Inspections Repetitive Eddy Airplanes Current and Visual Inspection Interval At whichever of the following occurs Thereafter at intervals (1) For Model later: not to exceed 100 414A airplanes, • Upon accumulating 8,500 hours hours TIS. serial numbers TIS on the airplane; 414A0001 through 414A0047 and • At the next inspection that would 414A0049 through have been required by emergency 414A0200. AD 2005-05-51 (required at intervals not to exceed 15 hours TIS); or • Within the next 2 days after receipt of this emergency AD. Thereafter at intervals not At whichever of the following occurs (2) For the to exceed 100 hours TIS. later: following airplanes that have • Upon accumulating 15,000 hours 15,000 hours or TIS on the airplane; more TIS or upon • At the next inspection that would accumulating have been required by emergency 15,000 hours TIS: AD 2005-05-51 (required at (i) All Model intervals not to exceed 15 hours 402C airplanes. TIS); or (ii) Model 414A • Within the next 2 days after airplanes, serial receipt of this emergency AD. numbers 414A0201 through 414A1212. 17

2005-05-52 3

Note: The Cessna service bulletins allow for either a visual inspection or eddy current inspection of the forward spars on all airplanes affected by this AD. Visual inspections of the forward spars do not satisfy the requirements of this AD for the airplanes referenced in paragraphs (f)(1) and (f)(2). These airplanes must have the forward spars inspected using the eddy current methods specified in the Cessna service bulletins. (i) Cracks Found: If you find any crack on any forward, aft, or auxiliary wing spar; or in surrounding structure such as spar webs or skins during any inspection required by this AD, before to further flight do the following: (1) Obtain an FAA-approved repair scheme from the Cessna Aircraft Company, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-5800, facsimile: (316) 942-9006; and (4) Incorporate this repair scheme. (h) Reporting Requirement: As soon as possible, but no later than 24 hours after any inspection required by this AD and as defined below: (1) Submit a report of inspection findings to the Manager, Wichita Aircraft Certification Office (ACO), by fax: (316) 946-4107. (i) Include a report for “cracks found” or “no cracks found” on the initial inspection; and (ii) Include a report only for “cracks found” on the repetitive inspections. (2) The report must include your name and a contact phone number, the results of the findings, a description of any cracking found, the airplane serial number, and the total number of hours TIS on the airplane. The “Lower Wing Spars and Skin Inspection Report” included in Cessna Service Bulletin MEB99-3 and MEB00-7 may be utilized for this reporting requirement. May I Request an Alternative Method of Compliance? (i) 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. (1) For information on any already approved alternative methods of compliance or for further information about this AD, contact Paul Nguyen, Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4125; facsimile: (316) 946-4107; e-mail: [email protected]. (2) Alternative methods of compliance that were approved for AD 2000-23-01 or emergency AD 2005-05-51 are not approved for this emergency AD. May I Get Copies of the Documents Referenced in this AD? (j) You may get copies of the documents referenced in this AD from the Cessna Aircraft Company, Product Support P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-5800; facsimile: (316) 942-9006. Issued in Kansas City, Missouri, on March 2, 2005. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. 18

BW 2005-05 THE CESSNA AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE EMERGENCY SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-05-53 THE CESSNA AIRCRAFT COMPANY: Directorate Identifier 2005-CE-10-AD. When Does This AD Become Effective? (c) This emergency AD becomes effective upon receipt. Are Any Other ADs Affected By This Action? (d) This action does not affect any other airworthiness directive. What Airplanes Are Affected by This AD? (c) This AD affects the following airplanes that are certificated in any category: Model 172R 172S 182T T182T

Serial Numbers 81234, 81235, and 81236. 89774, 89775, 89776, 89778 through 89781, 89783, 89784, 89786, 89788 through 89791, and 89793. 81522 through 81525 and 81537. 80353 through 80365, 80367, 80368, 80369, 80371, and 80372.

What is the Unsafe Condition Presented in This AD? (d) This AD is the result of flight control system problems found on airplanes within Cessna’s control that could also exist on airplanes produced and delivered within a certain time period. We are issuing this AD to prevent loss of airplane control due to incorrect or inadequate rigging of critical flight systems. Airplanes affected by this AD may have additional flight control issues beyond those listed in “What events caused this AD action?” What Must I do to Address This Problem? (e) The following specifies action you must do per this AD and other pertinent information to address this problem:

19

2005-05-53 2

Actions

Compliance

Procedures

Prior to further flight after (1) Do a one-time detailed inspection of the receipt of this emergency AD. the flight control system, correct installations that do not conform to type design, and repair any damage.

Follow Chapter 5 TIME LIMITS/ MAINTENANCE CHECKS of whichever of the following applies: • Model 172 Maintenance Manual using the List of Effective Pages, dated June 7, 2004. • Model 182/T182 Maintenance Manual using the List of Effective Pages, dated March 1, 2004.

Not applicable. (2) Special flight permits or positioning flights are not permitted for this AD.

14 CFR 39.19 allows special flight permits for all ADs, unless specifically prohibited in a specific AD. This emergency AD prohibits such flight permits. If an aircraft is in a location where necessary services are not available to perform the inspections identified above, contact Cessna Product Support at (316) 517-5800.

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. You may submit your request through your Flight Standards District Office (FSDO) Principal Inspector, who may add comments and then send your request to the Manager, Wichita Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance or for further information about this AD, contact Chris B. Morgan, Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4154; facsimile: (316) 946-4107; e-mail: [email protected]. Issued in Kansas City, Missouri, on March 4, 2005.

David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.

20

BW 2005-05 THE CESSNA AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE REVISION SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS

2005-05-53 R1 THE CESSNA AIRCRAFT COMPANY: Directorate Identifier 2005-CE-10-AD. When Does This AD Become Effective? (e) This emergency AD becomes effective upon receipt. Are Any Other ADs Affected By This Action? (f) This action does not affect any other airworthiness directive. What Airplanes Are Affected by This AD? (c) This AD affects the following airplanes that are certificated in any category: Model 172R 172S 182T T182T

Serial Numbers 17281234 through 17281236. 172S9774 through 172S9776, 172S9778 through 172S9781, 172S9783, 172S9784, 172S9786, 172S9788 through 172S9791, and 172S9793. 18281522 through 18281525, and 18281537. T18208353 through T18208365, T18208367 through T18208369, T18208371, and T18208372.

What is the Unsafe Condition Presented in This AD? (d) This AD is the result of flight control system problems found on airplanes within Cessna’s control that could also exist on airplanes produced and delivered within a certain time period. We are issuing this AD to prevent loss of airplane control due to incorrect or inadequate rigging of critical flight systems. Airplanes affected by this AD may have additional flight control issues beyond those listed in “What events caused this AD action?”

21

2005-05-53 R1 2

What Must I do to Address This Problem? (e) The following specifies action you must do per this AD and other pertinent information to address this problem:

Actions

Compliance

Procedures

Prior to further flight after (1) Do a one-time detailed inspection of the receipt of this emergency AD. the flight control system, correct installations that do not conform to type design, and repair any damage.

Follow Chapter 5 TIME LIMITS/ MAINTENANCE CHECKS of whichever of the following applies: • Model 172 Maintenance Manual using the List of Effective Pages, dated June 7, 2004. • Model 182/T182 Maintenance Manual using the List of Effective Pages, dated March 1, 2004.

Not applicable. (2) Special flight permits or positioning flights are not permitted for this AD.

14 CFR 39.19 allows special flight permits for all ADs, unless specifically prohibited in a specific AD. This emergency AD prohibits such flight permits. If an aircraft is in a location where necessary services are not available to perform the inspections identified above, contact Cessna Product Support at (316) 517-5800.

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. You may submit your request through your Flight Standards District Office (FSDO) Principal Inspector, who may add comments and then send your request to the Manager, Wichita Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance or for further information about this AD, contact Chris B. Morgan, Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4154; facsimile: (316) 946-4107; e-mail: [email protected]. Issued in Kansas City, Missouri, on March 5, 2005. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. 22