The B.F. Goodrich Company v. Aircraft Braking Systems Corporation, and Allied-Signal Incorporated, Defendants/cross-Appellants

72 F.3d 1577, 37 U.S.P.Q. 2d (BNA) 1314, 1996 U.S. App. LEXIS 80
CourtCourt of Appeals for the Federal Circuit
DecidedJanuary 4, 1996
Docket95-1112, 95-1120, and 95-1143
StatusPublished
Cited by82 cases

This text of 72 F.3d 1577 (The B.F. Goodrich Company v. Aircraft Braking Systems Corporation, and Allied-Signal Incorporated, Defendants/cross-Appellants) is published on Counsel Stack Legal Research, covering Court of Appeals for the Federal Circuit primary law. Counsel Stack provides free access to over 12 million legal documents including statutes, case law, regulations, and constitutions.

Bluebook
The B.F. Goodrich Company v. Aircraft Braking Systems Corporation, and Allied-Signal Incorporated, Defendants/cross-Appellants, 72 F.3d 1577, 37 U.S.P.Q. 2d (BNA) 1314, 1996 U.S. App. LEXIS 80 (Fed. Cir. 1996).

Opinion

LOURIE, Circuit Judge.

The B.F. Goodrich Co. (BFG) appeals from the judgment of the United States District Court for the District of Delaware holding (1) U.S. Patents 4,742,895 and 4,613,017 invalid under 35 U.S.C. §§ 103 and 102(b) and (2) that Aircraft Braking Systems Corp. (ABS) did not infringe either patent. ABS and Allied-Signal Inc. cross-appeal from the district court’s judgment that BFG did not engage in inequitable conduct, requesting that the court hold this to be an exceptional case and award them attorney fees under 35 U.S.C. § 285. B.F. Goodrich Co. v. Aircraft Braking Sys., C.A. Nos. 91-48/91-515-SLR (D.Del. Nov. 10, 1994). Because we conclude that the patents are invalid under 35 U.S.C. § 103 and that BFG did not engage in inequitable conduct, we affirm.

BACKGROUND

BFG is the assignee of the ’017 and ’895 patents. The ’017 patent is directed to a method of overhauling a disk brake assembly. The ’895 patent is a division of the ’017 patent and contains apparatus claims for a disk brake assembly. Both patents are entitled to the benefit of the ’017 patent’s July 2, 1984 filing date and thus July 2, 1983 is the critical date for purposes of 35 U.S.C. § 102.

The claimed brake assembly is used in aircraft landing gear wheels. Figure 4 of the patents is a cross-sectional view illustrating the assembly:

[[Image here]]

The assembly includes stators 46 positioned between rotors 50. The stators 46 and rotors 50 consist of carbon disks and are sandwiched between end plates 48. The rotors 50 are mechanically attached to a rim (not shown) on which is mounted a tire so that, when the wheel rotates, rotors 50 rotate between stators 46. When the brake is activated, piston 26’ applies pressure to one of the two end plates 48, which in turn forces together the rotors and stators against end plate 44 so that the resulting friction between the rotors and stators stops the 'wheel. Eventually, the carbon disks become worn through friction and must be replaced since a minimum thickness of the disks is required to absorb the heat generated by the friction and ensure effective braking operation.

The invention provides a brake assembly having alternating thick and thin disks, referred to as a thick/thin assembly, consisting of, for example, thin stators and thick rotors. The disks tend to wear evenly. Accordingly, when the thin disks become worn to the point of requiring replacement, the thick disks are only half worn. Only the original thin disks are replaced, and they are replaced with thick disks. The process can be repeated, and, during each maintenance interval, only half of the disks are thus replaced.

In comparison, prior art brake assemblies had disks of uniform thickness. During *1580 prosecution, the patentee distinguished its invention over this feature of the prior art brake assemblies. In response to a final rejection of the ’017 patent of the ground of obviousness, the applicant submitted an affidavit by Wesley S. Perry, Director of Engineering for BFG. The following are relevant portions of the Perry affidavit.

That ... he has not seen or heard of the brake construction and method shown and described in the [BFG patent application];
That as Director of Engineering he had the responsibility for reading the literature and trade journals on aircraft brakes and has attended numerous seminars and trade shows on aircraft brakes;
That at no time in the literature or at seminars and trade shows he has attended, has the brake construction and method shown and described in the [BFG patent application] been suggested;
That the common practice in overhauling carbon brakes is to replace all the brake disks after they are substantially completely worn with full thickness disks and that it would not be obvious to replace one set of stators or rotors with a new or refurbished set of full thickness disks while the other set is half worn at overhaul intervals shorter than the refurbished interval for the disks as taught and shown in the [BFG patent application];
That based on his observation and knowledge of the ordinary skilled worker overhauling carbon brakes, the ordinary skilled worker would not have found it expedient through routine experimentation to arrange the rotors and stators of a carbon disk brake with different available wear portions so that after a predetermined number of brake applications said available wear portions of a first group of disks are substantially worn away at an intermediate overhaul time and said available wear portions of a second group of disks are not worn away....

In response to the submission of this affidavit, the U.S. Patent and Trademark Office (PTO) allowed the application, which issued as the ’017 patent. The PTO subsequently allowed the divisional application, which issued as the ’895 patent. Claim 1 of the ’017 patent and claim 2 of the ’895 patent, which are the only independent claims at issue, read as follows:

1. A method of assembling and overhauling a disk brake having a plurality of disks with available wear portions of predetermined different thicknesses comprising positioning a first group of said disks in overlapping relationship with a second group of said disks, said first group of said disks having each of said available wear portions of a first thickness, said second group of said disks having each of said available wear portions of a second thickness, said first thickness of each of said available wear portions of said first group of said disks being less than said second thickness of each of said available wear portions of said second group of said disks, replacing said first group of said disks with a third group of said disks at an intermediate brake overhaul time when said available wear portions of said first group are substantially fully worn, said available wear portions of each of said third group of said disks having a third thickness greater than the thickness of each of said available wear portions of said second group of said disks at said intermediate brake overhaul time.
2. A disk brake assembly comprising a first group of brake disks and a second group of brake disks in axially aligned and interleaved relationship, said disks of said first group being interleaved with said disks of said second group in alternating relationship, each of said disks of said first group and said second group having oppositely disposed wear surfaces, said wear surfaces on opposite sides of each brake disk of said first group are equal in thickness, said wear surfaces on opposite sides of each brake disk of said second group are equal in thickness, said wear.

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72 F.3d 1577, 37 U.S.P.Q. 2d (BNA) 1314, 1996 U.S. App. LEXIS 80, Counsel Stack Legal Research, https://law.counselstack.com/opinion/the-bf-goodrich-company-v-aircraft-braking-systems-corporation-and-cafc-1996.