Airworthiness Directive · Amendment 39-14591 · Hamilton Sundstrand Model 14RF-9 Propellers
Hamilton Sundstrand Model 14RF-9 Propellers
This AD applies to Hamilton Sundstrand (formerly Hamilton Standard Division) model 14RF-9 propellers with propeller blades of the “+E” repair configuration (excludes “+E2” repair configuration) having serial numbers (SNs) below 885751. These propellers are installed on, but not limited to, Embraer 120 airplanes.
The FAA is adopting a new airworthiness directive (AD) for Hamilton Sundstrand model 14RF-9 propellers. This AD requires visual, feeler gage, and tap test inspections of certain serial number (SN) propeller blades of the "+E" repair configuration for blade delamination, and removing the blade from service if the blade fails inspection. This AD also requires removing those serial-numbered propeller blades from service by March 1, 2007. This AD results from reports of delaminated blade fiberglass repair patches that allowed corrosion to form on the aluminum blade spar under the patch. We are issuing this AD to prevent blade failure that could result in separation of a propeller blade and loss of control of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.
The “+E” blade marking can be found on the blade airfoil or stamped on the blade shank, adjacent to the blade and pin assembly part number.
(g) If the blade is stamped with “+E2” no further action is required.
For installed blades not previously inspected using Hamilton Sundstrand Alert Service Bulletin (ASB) No. 14RF-9-61-A143, dated November 21, 2005; or Revision 1, dated December 5, 2005; or ASB No. 14RF-9-61-A144, dated February 27, 2006; or ASB No. 14RF-9-61-A145, dated April 13, 2006; or ASB No. 14RF-9-61-146, dated April 3, 2006, do the following:
(1) Perform initial visual, feeler gage, and tap test inspections for delamination within 10 flight cycles or 5 days after the effective date of this AD, whichever occurs first.
(2) Use paragraph 3 of the Accomplishment Instructions of Hamilton Sundstrand ASB No. 14RF-9-61-A145, dated April 13, 2006, to do the inspection.
(i) For installed blades that have not been reinspected using Hamilton Sundstrand ASB No. 14RF-9-61-A143, dated November 21, 2005; or Revision 1, dated December 5, 2005; or ASB No. 14RF-9-61-A144, dated February 27, 2006; or ASB No. 14RF-9-61-A145, dated April 13, 2006; or ASB No. 14RF-9-61-A146, dated April 3, 2006, do the following:
(1) Perform a 2nd inspection of installed blades for delamination after accumulating an additional 500 flight cycles or by July 1, 2006, whichever occurs first.
(2) Use paragraph 3 of the Accomplishment Instructions of Hamilton Sundstrand ASB No. 14RF-9-61-A145, dated April 13, 2006, to do the inspection.
For blades being installed after the effective date of this AD that were not previously inspected using Hamilton Sundstrand ASB No. 14RF-9-61-A143, dated November 21, 2005; or Revision 1, dated December 5, 2005; or ASB No. 14RF-9-61-A144, dated February 27, 2006; or ASB No. 14RF-9-61-A145, dated April 13, 2006, do the following:
(1) Before installing the blade, perform initial visual, feeler gage, and tap test inspections for delamination. Use paragraph 3. of the Accomplishment Instructions of Hamilton Sundstrand ASB No. 14RF-9-61-A146, dated April 3, 2006, to do the inspection.
(2) Perform a 2nd inspection for delamination at least 7 days after installing the blade, but no later than 60 days after the initial inspection. Use paragraph 3. of the Accomplishment Instructions of Hamilton Sundstrand ASB No. 14RF-9-61-A146, dated April 3, 2006, to do the inspection.
Before further flight, remove propeller blades from service that fail inspection.
By March 1, 2007, remove from service all blades of the “+E” repair configuration having SNs below 885751.
(m) After March 1, 2007, do not install any blades of the “+E” repair configuration having SNs below 885751, onto any propeller.
(n) Hamilton Sundstrand ASB No. 14RF-9-61-A147, dated April 19, 2006, contains information on upgrading the removed blades to the “+E2” repair configuration.
Within 10 days after each blade inspection, record the inspection data on a copy of the data sheet. The data sheet is on page 10 of ASB No. 14RF-9-61-A145, dated April 13, 2006, and ASB No. 14RF-9-61-A146, dated April 3, 2006. Report the inspection data to Hamilton Sundstrand, fax (800) 654-5107, and Boston Aircraft Certification Office, fax (781) 238-7170. The Office of Management and Budget (OMB) approved the reporting requirements and assigned OMB control number 2120-0056.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Propellers
