DETAILED ACTION
Notice of Pre-AIA or AIA Status
The present application, filed on or after March 16, 2013, is being examined under the first inventor to file provisions of the AIA .
Remarks
This communication is in response to Application No. 19/054,391 filed on 02/14/2025.
Claims 21-40 are currently pending and have been examined.
This application is a continuation of U.S. application No. 18/431,882 filed on 02-02/2024 now U.S Patent 12,228,039 and U.S. application No. 17/808,286 filed on 06-22-2022 now U.S Patent 11,927,104. See MPEP 201.07. In accordance with MPEP 609.02 A.2 and MPEP 2001.06 (b) (last paragraph), the Examiner has reviewed and considered the prior art cited in the Parent Application.
Also in accordance with MPEP 2001.06 (b) (last paragraph), all documents cited or considered ‘of record’ in the Parent Application are now considered cited or ‘of record’ in this application.
Additionally, Applicant(s) are reminded that a listing of the information cited or ‘of record’ in the Patent Application need not be resubmitted in this application unless Applicants desire the information to be printed on a patent issuing from this application. See MPEP 609.02 A. 2. Finally, Applicants are reminded that the prosecution history of the parent application(s) is/are relevant in this application.
Information Disclosure Statement
The information disclosure statement (IDS) submitted on 11/17/2025 is in compliance with the provisions of 37 CFR 1.97. Accordingly, the information disclosure statement is being considered by the examiner.
Drawings
The drawings filed 02/14/2025 are acceptable.
Claim Interpretation Under 35 USC § 112
No claim elements in this application are presumed to invoke 35 U.S.C. 112(f).
Double Patenting
The nonstatutory double patenting rejection is based on a judicially created doctrine grounded in public policy (a policy reflected in the statute) so as to prevent the unjustified or improper timewise extension of the “right to exclude” granted by a patent and to prevent possible harassment by multiple assignees. A nonstatutory double patenting rejection is appropriate where the conflicting claims are not identical, but at least one examined application claim is not patentably distinct from the reference claim(s) because the examined application claim is either anticipated by, or would have been obvious1 over, the reference claim(s). See, e.g., In re Berg, 140 F.3d 1428, 46 USPQ2d 1226 (Fed. Cir. 1998); In re Goodman, 11 F.3d 1046, 29 USPQ2d 2010 (Fed. Cir. 1993); In re Longi, 759 F.2d 887, 225 USPQ 645 (Fed. Cir. 1985); In re Van Ornum, 686 F.2d 937, 214 USPQ 761 (CCPA 1982); In re Vogel, 422 F.2d 438, 164 USPQ 619 (CCPA 1970); In re Thorington, 418 F.2d 528, 163 USPQ 644 (CCPA 1969).
A timely filed terminal disclaimer in compliance with 37 CFR 1.321(c) or 1.321(d) may be used to overcome an actual or provisional rejection based on nonstatutory double patenting provided the reference application or patent either is shown to be commonly owned with the examined application, or claims an invention made as a result of activities undertaken within the scope of a joint research agreement. See MPEP § 717.02 for applications subject to examination under the first inventor to file provisions of the AIA as explained in MPEP § 2159. See MPEP §§ 706.02(l)(1) - 706.02(l)(3) for applications not subject to examination under the first inventor to file provisions of the AIA . A terminal disclaimer must be signed in compliance with 37 CFR 1.321(b).
The USPTO Internet website contains terminal disclaimer forms which may be used. Please visit www.uspto.gov/patent/patents-forms. The filing date of the application in which the form is filed determines what form (e.g., PTO/SB/25, PTO/SB/26, PTO/AIA /25, or PTO/AIA /26) should be used. A web-based eTerminal Disclaimer may be filled out completely online using web-screens. An eTerminal Disclaimer that meets all requirements is auto-processed and approved immediately upon submission. For more information about eTerminal Disclaimers, refer to www.uspto.gov/patents/process/file/efs/guidance/eTD-info-I.jsp.
Claims 21-40 are rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1-16 of U.S. Patent No. 11,927,104 (17/808,286). Although the claims at issue are not identical, they are not patentably distinct from each other because the claim requirements of claims 21-40 of the instant application are disclosed in claims 1-16 of U.S. Patent No. 11,927,104.
Instant application
U.S Patent 11,927,104 (17/808,286)
21. (New) An aircraft engine sensing apparatus comprising:
a plurality of connection wires connecting an aircraft engine sensor to a sensor connector,
wherein the plurality of connection wires are positioned within a wire protection housing;
at least one ceramic insulator positioned within the wire protection housing and defining a plurality of insulator openings,
wherein each of the plurality of connection wires passes through one of the plurality of insulator openings,
wherein the at least one ceramic insulator is positioned between the aircraft engine sensor and the sensor connector; and
a plurality of glass insulators, wherein at least some of the plurality of glass insulators are positioned between
the at least one ceramic insulator and at least one of the plurality of connection wires.
1. An aircraft engine sensing apparatus comprising:
an aircraft engine sensor positioned within an aircraft engine;
a plurality of connection wires connecting the aircraft engine sensor to a sensor connector,
wherein the plurality of connection wires are positioned within a wire protection housing;
at least one ceramic insulator positioned within the wire protection housing and defining a plurality of insulator openings,
wherein each of the plurality of connection wires passes through one of the plurality of insulator openings,
wherein the at least one ceramic insulator is positioned between the aircraft engine sensor and the sensor connector; and
a plurality of glass insulators, wherein at least some of the plurality of glass insulators are positioned between
an inner surface of the wire protection housing and an outer surface of the at least one ceramic insulator.
16. the at least one ceramic insulator and at least one of the plurality of connection wires
22. (New) The aircraft engine sensing apparatus of claim 21, wherein the aircraft engine sensor is positioned within an aircraft engine and comprises a rotational speed sensor.
2. The aircraft engine sensing apparatus of claim 1, wherein the aircraft engine sensor comprises a rotational speed sensor.
23. (New) The aircraft engine sensing apparatus of claim 22,
wherein the aircraft engine comprises an engine shaft and a toothed wheel secured to the engine shaft.
3. The aircraft engine sensing apparatus of claim 2,
wherein the aircraft engine comprises an engine shaft and a toothed wheel secured to the engine shaft, ….
24. (New) The aircraft engine sensing apparatus of claim 23,
wherein the engine shaft passes through a central opening of the toothed wheel, wherein the rotational speed sensor is positioned adjacent to the toothed wheel.
3. The aircraft engine sensing apparatus of claim 2, … wherein the engine shaft passes through a central opening of the toothed wheel, wherein the rotational speed sensor is positioned adjacent to the toothed wheel.
25. (New) The aircraft engine sensing apparatus of claim 22,
wherein the aircraft engine comprises an engine shaft and a driven gear secured to the engine shaft.
4. The aircraft engine sensing apparatus of claim 2, wherein the aircraft engine comprises an engine shaft and a driven gear secured to the engine shaft, wherein the engine shaft passes through a central opening of the driven gear, wherein the rotational speed sensor is positioned adjacent to the driven gear.
26. (New) The aircraft engine sensing apparatus of claim 25, wherein the engine shaft passes through a central opening of the driven gear, wherein the rotational speed sensor is positioned adjacent to the driven gear.
4. The aircraft engine sensing apparatus of claim 2, wherein the aircraft engine comprises an engine shaft and a driven gear secured to the engine shaft, wherein the engine shaft passes through a central opening of the driven gear, wherein the rotational speed sensor is positioned adjacent to the driven gear.
27. (New) The aircraft engine sensing apparatus of claim 22, wherein the aircraft engine sensor is positioned within a sensor protection housing.
5. The aircraft engine sensing apparatus of claim 1, wherein the aircraft engine sensor is positioned within a sensor protection housing.
28. (New) The aircraft engine sensing apparatus of claim 27, wherein the sensor protection housing is secured to an inner engine casing of the aircraft engine.
6. The aircraft engine sensing apparatus of claim 5, wherein the sensor protection housing is secured to an inner engine casing of the aircraft engine.
29. (New) The aircraft engine sensing apparatus of claim 27, wherein the sensor protection housing is welded to the wire protection housing.
7. The aircraft engine sensing apparatus of claim 5, wherein the sensor protection housing is welded to the wire protection housing.
30. (New) The aircraft engine sensing apparatus of claim 22, wherein at least a portion of the wire protection housing is positioned within the aircraft engine.
8. The aircraft engine sensing apparatus of claim 1, wherein at least a portion of the wire protection housing is positioned within the aircraft engine.
31. (New) The aircraft engine sensing apparatus of claim 22, wherein the sensor connector is positioned within a connector protection housing.
10. The aircraft engine sensing apparatus of claim 1, wherein the sensor connector is positioned within a connector protection housing.
32. The aircraft engine sensing apparatus of claim 31, wherein the connector protection housing is positioned on an engine casing of the aircraft engine.
11. The aircraft engine sensing apparatus of claim 10, wherein the connector protection housing is positioned on an engine casing of the aircraft engine.
33. (New) The aircraft engine sensing apparatus of claim 31, wherein the connector protection housing is welded to the wire protection housing.
12. The aircraft engine sensing apparatus of claim 10, wherein the connector protection housing is welded to the wire protection housing.
34. (New) The aircraft engine sensing apparatus of claim 31, wherein the sensor connector comprises a plurality of sensor output pins, wherein each of the plurality of connection wires is connected to one of the plurality of sensor output pins.
13. The aircraft engine sensing apparatus of claim 10, wherein the sensor connector comprises a plurality of sensor output pins, wherein each of the plurality of connection wires is connected to one of the plurality of sensor output pins.
35. (New) The aircraft engine sensing apparatus of claim 21, wherein the plurality of connection wires and the wire protection housing comprise metal material.
36. (New) The aircraft engine sensing apparatus of claim 21, wherein the at least one ceramic insulator comprises at least one of alumina ceramic material or glass-ceramic material.
14. The aircraft engine sensing apparatus of claim 1, wherein the at least one ceramic insulator comprises at least one of alumina ceramic material or g lass-ceramic material.
37. (New) The aircraft engine sensing apparatus of claim 21, wherein an outer surface of the at least one ceramic insulator is in contact with an inner surface of the wire protection housing.
15. The aircraft engine sensing apparatus of claim 1, wherein the outer surface of the at least one ceramic insulator is in contact with the inner surface of the wire protection housing.
38. (New) The aircraft engine sensing apparatus of claim 21,
wherein at least some of the plurality of glass insulators are positioned between an inner surface of the wire protection housing and an outer surface of the at least one ceramic insulator.
1. … a plurality of glass insulators,
wherein at least some of the plurality of glass insulators are positioned between an inner surface of the wire protection housing and an outer surface of the at least one ceramic insulator.
39. (New) The aircraft engine sensing apparatus of claim 21 further comprising a plurality of ceramic insulators.
40. (New) The aircraft engine sensing apparatus of claim 39, wherein at least some of the plurality of glass insulators are positioned between the plurality of ceramic insulators.
16. The aircraft engine sensing apparatus of claim 1, wherein at least some of the plurality of glass insulators are positioned between the at least one ceramic insulator and at least one of the plurality of connection wires.
Conclusion
The prior art made of record on the attached PTOL-892 and not relied upon is considered pertinent to applicant's disclosure as each further discloses a state of the art.
The examiner has pointed out particular references contained in the prior art of record in the body of this action for the convenience of the applicant. Although the specified citations are representative of the teachings in the art and are applied to the specific limitations within the individual claim, other passages and figures may apply as well. Applicant should consider the entire prior art as applicable as to the limitations of the claims. It is respectfully requested from the applicant, in preparing the response, to consider fully the entire reference as potentially teaching all or part of the claimed invention, as well as the context of the passage as taught by the prior art or pointed out by the examiner.
Inquiry
Any inquiry concerning this communication or earlier communications from the examiner should be directed to J. T. Newton, Esq. whose telephone number is (313)446-4899. The examiner can normally be reached 0700-1500 M-F.
Examiner interviews are available via telephone, in-person, and video conferencing using a USPTO supplied web-based collaboration tool. To schedule an interview, applicant is encouraged to use the USPTO Automated Interview Request (AIR) at http://www.uspto.gov/interviewpractice.
If attempts to reach the examiner by telephone are unsuccessful, the examiner’s supervisor, SPE Justin Mikowski can be reached at (571) 272-8525. The fax phone number for the organization where this application or proceeding is assigned is 571-273-8300.
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/J. T. Newton/Primary Examiner, Art Unit 3673 17 February 2026