AIRWORTHINESS DIRECTIVE

CAA-AD-T-027/2002

Supersedes CAA-AD-T-019/2002

Date of issue: February 21, 2002

PROPPELER - BLADE - REPLACEMENT

Applicability: This airworthiness directive (AD) is applicable to Hamilton Sundstrand Corporation (formerly Hamilton Standard Division) model 568F-1 propellers installed with blades, part numbers (P/N’s) R815505-2 and R815505-3, that have a serial number (SN) of FR1698 or lower. These propellers are installed on, but not limited to, Aerospatiale ATR 42-400 and -500 and ATR 72-212 and -500 airplanes.

Effective date: Upon receipt.

Compliance: Required as indicated in FAA E AD 2002-04-52.

Remarks: The compliance of this AD must be recorded in Aircraft Logbook, where applicable the requirements of this AD must be integrated into Aircraft Technical Documentation. Address inquiries concerning this AD to: Civil Aviation Authority, Airworthiness Division, Ruzyne Airport, 160 08 Prague 6, Czech Republic, tel.: 420 2 33320922, fax: 420 2 20562270.

Ing. Pavel MATOUŠEK

Director of Airworthiness Division

CAA CZ

EMERGENCY AIRWORTHINESS DIRECTIVE

2002-04-52 Hamilton Sundstrand Corporation: Docket No. 2002-NE-02-AD. Supersedes Emergency AD 2002-03-51 issued on February 7, 2002.

Applicability:

This airworthiness directive (AD) is applicable to Hamilton Sundstrand Corporation (formerly Hamilton Standard Division) model 568F-1 propellers installed with blades, part numbers (P/N’s) R815505-2 and R815505-3, that have a serial number (SN) of FR1698 or lower. These propellers are installed on, but not limited to, Aerospatiale ATR 42-400 and -500 and ATR 72-212 and -500 airplanes.

Note 1: AD applies to each propeller identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For propellers that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance:

Compliance with this AD is required as indicated, unless already done.

To prevent blade failure due to corrosion-induced fatigue, which could result in blade separation and possible loss of airplane control, do the following:

(a) For propeller blades P/N’s R815505-2 and R815505-3, replace the blade using the SN range and compliance times specified in the following Table:

Blade Removal Time Requirements

If the SN of the propeller blade is -	Then replace the blade by the earlier of -
(1) Lower than FR183.	Eight days or 80 flight hours (FH) after receipt of Emergency AD 2002-03-51.
(2) FR 183 to FR265.	Twenty-one days or 210 FH after receipt of Emergency AD 2002-03-51.
(3) FR266 to FR341.	Thirty-six days or 360 FH after receipt of Emergency AD 2002-03-51.
(4) FR342 to FR428.	Fifty-two days or 520 FH after receipt of Emergency AD 2002-03-51.

(b) Procedures for removing the propeller blade and installing a serviceable blade can be found in Hamilton Sundstrand Maintenance Manual P5206.

(c) Within 180 flight hours or 18 days after receipt of this AD, for propeller blades P/N’s R815505-2 and R815505-3, that have a SN of FR1698 or lower, perform an ultrasonic shear wave inspection of the blade tulip in accordance with the Accomplishment Instructions of Hamilton Sundstrand ASB 568F-61-A35, dated February 15, 2002, and remove blades with unacceptable indications in accordance with the ASB.

Alternative Methods of Compliance

(d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Boston Aircraft Certification Office (ACO). Operators must submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Boston ACO.

Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Boston ACO.

Special Flight Permits

(e) Special limited 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) for a nonrevenue flight to a location where the requirements of this AD can be done.

Effective Date

(f) Emergency AD 2002-04-52, issued February 15, 2002, becomes effective upon receipt.

FOR FURTHER INFORMATION CONTACT: Frank Walsh, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-7158; fax (781) 238-7170.

Issued in Burlington, Massachusetts on February 15, 2002.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.