FAA orders · airworthiness directive · current

2001-13-03 R1: Flap clevis

FAA order 2001-13-03 R1 is an airworthiness directive in force since May 27, 2003. The FAA's subject line: Flap clevis. It names Kaman Aerospace Corp K-1200: about 17 aircraft on the U.S. register today, though an order usually covers particular versions or serial numbers rather than every one. System: flight controls.

What it applies to as the FAA lists it

Kind of product: Aircraft
Makes: Kaman Aerospace Corporation
Models: K-1200
On this site: Kaman Aerospace Corp K-1200 17 registered

Dates and paperwork

In force since: May 27, 2003
Published: April 21, 2003 (signed April 9, 2003)
Docket: 2000-SW-50-AD
Replaces: 2001-13-03
Status: Current
The FAA's document: Read the order on the FAA's site

The FAA's summary their words, unchanged

This amendment revises an existing airworthiness directive (AD) for Kaman Aerospace Corporation (Kaman) Model K-1200 helicopters that currently requires reducing the life limit of the rotor shaft and teeter pin assembly and establishing a life limit for the flap clevis. This amendment retains those requirements but removes a flap clevis part number from the applicability and, as a result of a comment, changes the application of the life limit from the flap clevis to the flap clevis assembly. This amendment is prompted by the determination after an analysis of testing results that a certain flap clevis assembly should have an unlimited life. The actions specified by this revision are intended to remove the life limit for a specified flap clevis assembly. The actions specified by this AD are intended to prevent fatigue failure of the rotor shaft, teeter pin assembly, and flap clevis assembly, and subsequent loss of control of the helicopter.

The order itself the regulatory text, as published

Show the full text (2,861 characters)

2001-13-03 R1 Kaman Aerospace Corporation: Amendment 39-13123. Docket No. 2000-SW-50-AD. Revises AD 2001-13-03, Amendment 39-12283, Docket No. 2000-SW-50-AD. 

	Applicability: Model K-1200 helicopters, certificated in any category. 

	Note 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters 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 2 accordance with paragraph (c) 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: Required as indicated, unless accomplished previously. 

	To prevent failure of the rotor shaft, teeter pin assembly, or flap clevis due to fatigue cracks, and subsequent loss of control of the helicopter, accomplish the following: 

	(a) Before further flight, remove any rotor shaft, part number (P/N) K974112-001, -003, -005, -007, -009, or -101, that has 3,750 or more hours time-in-service (TIS) and replace it with an airworthy part. Remove any teeter pin assembly, P/N K910005-007 or -009, that has 550 or more hours TIS and replace it with an airworthy part. Remove any flap clevis assembly, P/N K911049-001, -003, or -005, that has 640 or more hours TIS, and replace it with an airworthy part. 

	(b) This AD revises the Limitations section of the maintenance manual by removing the life limit of 640 hours TIS established for the flap clevis, P/N K911049-021. The life limit for each rotor shaft, P/N K974112-001, -003, -005, -007, -009, and -101 remains at 3,750 hours TIS; the life limit for each teeter pin assembly, P/N K910005-007 and -009, remains at 550 hours TIS; and the life limit for each flap clevis assembly, P/N K911049-001, -003, and -005 remains at 640 hours TIS. 

	(c) 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, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Boston Aircraft Certification Office. 

	Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Boston Aircraft Certification Office. 

	(d) Special flight permits will not be issued. 

	(e) This amendment becomes effective on May 27, 2003.

Source: FAA Dynamic Regulatory System, airworthiness directives. The FAA's document is the authority; the register counts are this site's, from the FAA register of October 5, 2026. Connections as data: /graph/directive/2001-13-03 R1.json · aircraft systems.