Congressional Air, Ltd. v. Beech Aircraft Corp.

176 F.R.D. 513, 40 Fed. R. Serv. 3d 678, 1997 U.S. Dist. LEXIS 20908, 1997 WL 751804
CourtDistrict Court, D. Maryland
DecidedNovember 13, 1997
DocketCiv. A. No. DKC 96-2322
StatusPublished
Cited by6 cases

This text of 176 F.R.D. 513 (Congressional Air, Ltd. v. Beech Aircraft Corp.) is published on Counsel Stack Legal Research, covering District Court, D. Maryland primary law. Counsel Stack provides free access to over 12 million legal documents including statutes, case law, regulations, and constitutions.

Bluebook
Congressional Air, Ltd. v. Beech Aircraft Corp., 176 F.R.D. 513, 40 Fed. R. Serv. 3d 678, 1997 U.S. Dist. LEXIS 20908, 1997 WL 751804 (D. Md. 1997).

Opinion

MEMORANDUM OPINION AND ORDER GRANTING DEFENDANT’S MOTION TO STRIKE PLAINTIFF’S EXPERT’S NEW REPORT

DAY, United States Magistrate Judge.

Defendant, Beech Aircraft Corporation (“Beech”), filed Beech’s Motion to Strike Plaintiffs Expert’s New Report (“Defendant’s Motion”) in an effort to exclude a report filed by plaintiffs expert, Dr. Douglas Chisholm, prepared on September 24, 1997 and served upon Beech on October 17, 1997. The Court has considered Defendant’s Motion, the opposition and reply thereto, and deems that no hearing is necessary. Local [514]*514Rule 105.6 (D.Md.) The Court GRANTS Defendant’s Motion for the reasons set forth below.

I. The September 24,1997 Report Was Not Timely Served.

The parties made timely disclosures of their initial expert’s reports pursuant to Fed. R.Civ.P. 26(a)(2) and the Scheduling Orders issued by the Court. Plaintiff, Congressional Air Limited, (“Congressional”), produced a January 21, 1997 expert report prepared by Dr. Chisholm, which sets forth five points under a section entitled, “Conclusions and Opinions.” Of particular interest are points 4 and 5.

4. But for the presence of the defectively designed hole for the grease fitting, the fatigue cracks would not have initiated and propagated to a critical size causing the rod end to fracture in normal use.
5. The defective and unreasonably dangerous design of nose gear rod end was the sole proximate cause of the failure of the component, the failure to extend and lock the landing gear, and the subsequent damage to the aircraft.

Expert report of Dr. Chisholm, dated January 21, 1997, p. 3. Dr. Chisholm unequivocally concludes that the part in question, the nose gear rod end bearing, failed as the result of its negligent design.

The discovery deadline, originally set for March 25, 1997, was extended to April 25, 1997, in deference to the joint request of the parties based upon the “handling and transfer of the part for inspection by expert witnesses, which has lengthened the process of obtaining expert reports” and to allow time for depositions. Upon receipt and review of Dr. Chisholm’s report, Beech felt confident in its ability to defend against the claims, so much so that Beech decided against pursuing depositions or other discovery regarding the basis for Dr. Chisholm’s opinions.

Beech’s Rule 26(a)(2) expert disclosures were due on or before March 21, 1997. Beech timely filed the report of its expert, Charles R. Morin. Mr. Morin’s report essentially attributes the failure of the rod end bearing to “a prior overload event followed by low cycle fatigue crack propagation.” He further opines “there is no evidence of a defect in design or manufacturing.” Expert report of Mr. Morin (undated) p. 5, (emphasis added).

On September 10, 1997, Dr. Chisholm received additional discovery materials, conducted further examinations and submitted an additional report dated September 24, 1997. In his analysis of these materials, Dr. Chisholm states in Section B of his report,

The disclosure of two (2) prior accidents (C-16.0), involving the subject aircraft as well as the report of C. Morin (C-17.0), and the Beech Aircraft Company (BAC) analysis of static and dynamic loads on the landing gear components and rod' end specifications prompted the author to examine the load path associated with a partial landing gear deployment and crash landing.
An examination of BAC landing gear drawings (C-12.0) revealed that under the conditions of a partial deployment/landing scenario, the rod ends, rods and gear train are all loaded in compression not tension, as suggested in Morin’s report (C-17.0). As a consequence of this compression loading, a so called “pop in” crack (created under tensile loads) is not possible. Further, any bending loads which have both tensile and compressive components would be most unlikely to produce the symmetry observed at the edges of the grease fitting hole under any realistic compression load induced landing gear failure (there is no evidence of a bending load failure in the part).
No satisfactory explanation of the failure can be forthcoming from the above theory, and therefore, a further examination was conducted.

Expert report of Dr. Chisholm, dated September 24, 1997, p. 2. In Section E, entitled “Analysis of the Failure,” Dr. Chisholm makes reference to “material defects (cracks and inclusions),” ... “anomalies in material” and other factors that “are believed to be the cause of the subject rod end failure.” Not surprisingly, his “Conclusions and Opinions” [515]*515now include suggestions of negligence in manufacturing.1

A careful review of the original and subsequent opinions of Dr. Chisholm lead to the firm conviction that the September 24, 1997 report is “intended solely to contradict or rebut” the report prepared by Mr. Morin. This view is supported by references in Congressional’s memorandum in opposition to Defendant’s Motion, which state that “[o]n September 24, 1997, Dr. Chisholm amended his earlier report after reinspecting the nose gear end rod bearing and reviewing Mr. Morin’s report.” The opposition further notes that “Dr. Chisholm amended his report after reviewing the work of defendant’s experts and then re-examining the effective nose gear end rod.” Under these circumstances, the use of Dr. Chisholm’s September 24,1997 report on behalf of Congressional is governed by Fed.R.Civ.P. 26(a)(2)(C), which required the disclosure of such a report within 30 days after the disclosure of Mr. Morin’s report on behalf of Beech. The rules regarding the disclosure of expert testimony states,

These disclosures shall be made at the times and in the sequence directed by the Court. In the absence of other directions from the Court or stipulation by the parties, the disclosures shall be made at least 90 days before the trial date or the date the case is to be ready for trial or, if the evidence is intended solely to contradict or rebut evidence on the same subject matter identified by another party under paragraph (2)(B), within SO days after the disclosure made by the other party. The parties shall supplement the disclosures when required under subdivision (e)(1).

Fed.R.Civ.P. 26(a)(2)(C) (emphasis added). Since the subsequent report of Dr. Chisholm is being used to rebut Mr. Morin’s report, plaintiff was required to disclose the subsequent report within 30 days of the receipt of Mr. Morin’s report. See Fuller v. Volvo GM Heavy Truck Corp., 1995 WL 489542 (N.D.Ill.1995). The rule uses the term “shall” and is mandatory upon the parties. Congressional was obligated to provide this report in a timely fashion.

If Rule 26(a)(2)(C) and the Court’s Scheduling Orders are followed properly, the parties will have ample time to conduct discovery, obtain additional rebuttal experts and/or opinions, and to submit any necessary supplementations of discovery.

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176 F.R.D. 513, 40 Fed. R. Serv. 3d 678, 1997 U.S. Dist. LEXIS 20908, 1997 WL 751804, Counsel Stack Legal Research, https://law.counselstack.com/opinion/congressional-air-ltd-v-beech-aircraft-corp-mdd-1997.