Office Action 2: Notice of Allowance (2025-01-23)

CLAIMS:
Amendments to the Claims:

This listing of claims will replace all prior versions, and listings, of claims in the application:

Claims 1-11. (Cancelled)210

12\. (Currently Amended) A rotorcraft comprising:
a fuselage forming a cabin with a cabin floor, the fuselage comprising a lower shell, a side shell, and at least one lateral longeron which together delimit at least one lower lateral fuselage compartment with an opening; and
at least one non-retractable wheel-type landing gear rigidly attached in the at least one lower lateral fuselage compartment and extending at least partly through the opening, the at least one non-retractable wheel-type landing gear comprising:at least one wheel;
a shock absorber with a length axis and a circumferential direction, the shock absorber being connected to the at least one wheel and comprising:
a shock absorber tube, and a shock absorber rod telescopically mounted to the shock absorber tube;
a mounting arm extending laterally from the shock absorber tube, the mounting arm being integrally formed with the shock absorber tube and rigidly attached to a first fitting mounted to the cabin floor and the at least one lateral longeron; and
a link fixation extending laterally from the shock absorber tube, the link fixation being arranged in the circumferential direction of the shock absorber at an
SVG {EMBED HERE} 0.0470.047

angle in a range from 450 to 1200 with respect to the mounting arm and rigidly attached via a linear link component to a second fitting mounted to the lower shell of the rotorcraft.

13\. (Original) The rotorcraft of The rotorcraft of
wherein the at least one non-retractable wheel- type landing gear further comprises another link fixation extending laterally from the shock absorber tube, the other link fixation being arranged in the circumferential direction of the shock absorber at an angle in a range from 450 to 1200 with respect to the link fixation and rigidly attached via a triangular link component to a third fitting mounted to the lower shell of the rotorcraft.

14\. (Original) The rotorcraft of The rotorcraft of
wherein the triangular link component is arranged tangentially to the lower shell.

15\. (Original) The rotorcraft of The rotorcraft of
wherein the linear link component is arranged tangentially to the lower shell.

16\. (New) The rotorcraft of The rotorcraft of
wherein the link fixation is integrally formed with the shock absorber tube and provided for attachment to the linear link component adapted for linking the shock absorber tube to the second fitting of the rotorcraft.

17\. (New) The rotorcraft of The rotorcraft of
wherein the other link fixation is integrally formed with the shock absorber tube and provided for

attachment to the triangular link component adapted for linking the shock absorber tube to the third fitting of the rotorcraft.

18\. (New) The rotorcraft of The rotorcraft of
wherein the link fixation and the other link fixation span in a horizontal plane that is positioned at an angle in a range from 800 to 1000 with respect to the length axis of the shock absorber.

19\. (New) The rotorcraft of The rotorcraft of
wherein the mounting arm and the other link fixation span in a vertical plane that is oriented at least approximately perpendicular to the horizontal plane.

20\. (New) The rotorcraft of The rotorcraft of
wherein the shock absorber tube comprises a closed end and an axially opposed open end, wherein the mounting arm is provided close to the closed end, and wherein the link fixation is provided close to the open end.

21\. (New) The rotorcraft of The rotorcraft of
wherein the shock absorber tube comprises a closed end and an axially opposed open end, wherein the mounting arm is provided close to the closed end, and wherein the link fixation and the other link fixation are provided close to the open end.

22\. (New) The rotorcraft of The rotorcraft of
wherein the other link fixation forms a hinge axis that is at least approximately arranged perpendicular to the mounting arm.

23\. (New) The rotorcraft of The rotorcraft of
wherein the mounting arm is rigidly attachable via a single hinge to a single attachment point provided on the first fitting of the rotorcraft, and wherein the single hinge forms a single hinge axis that is at least approximately arranged perpendicular to the mounting arm.

24\. (New) The rotorcraft of The rotorcraft of
wherein the hinge axis and the single hinge axis are at least approximately arranged in parallel.

25\. (New) A rotorcraft comprising:
a fuselage with a cabin with a cabin floor, the fuselage comprising a lower shell, a side shell, and a longeron which together delimit a lower lateral fuselage compartment with an opening; and
a non-retractable wheel landing gear attached in the lower lateral fuselage compartment and extending at least partly through the opening, the non-retractable wheel landing gear comprising:a wheel;
a shock absorber with a length axis and a circumferential direction, the shock absorber being connected to the wheel and comprising:
a shock absorber tube, and a shock absorber rod telescopically mounted to the shock absorber tube;
a mounting arm extending from the shock absorber tube, the mounting arm attached to a first fitting mounted to the cabin floor and the lateral longeron; and

a link fixation extending from the shock absorber tube, the link fixation being arranged in the circumferential direction of the shock absorber at an angle in a range from 450 to 1200 with respect to the mounting arm and attached via a linear link component to a second fitting mounted to the lower shell of the rotorcraft.
26\. (New) The rotorcraft of The rotorcraft of SVG {EMBED HERE} 0.0470.047
wherein the non-retractable wheel landing gear further comprises another link fixation extending from the shock absorber tube, the other link fixation being arranged in the circumferential direction of the shock absorber at an angle in a range from 450 to 1200 with respect to the link fixation and attached via a triangular link component to a third fitting mounted to the lower shell of the rotorcraft.

27\. (New) The rotorcraft of The rotorcraft of
wherein at least one of the triangular link component and the linear link component is arranged tangentially to the lower shell.

28\. (New) The rotorcraft of The rotorcraft of
wherein the link fixation is integrally formed with the shock absorber tube and provided for attachment to the linear link component adapted for linking the shock absorber tube to the second fitting of the rotorcraft.

29\. (New) The rotorcraft of The rotorcraft of
wherein the other link fixation is integrally formed with the shock absorber tube and provided for

attachment to the triangular link component adapted for linking the shock absorber tube to the third fitting of the rotorcraft.

30\. (New) The rotorcraft of The rotorcraft of
wherein the link fixation and the other link fixation span in a horizontal plane that is positioned at an angle in a range from 800 to 1000 with respect to the length axis of the shock absorber, and wherein the mounting arm and the other link fixation span in a vertical plane that is oriented approximately perpendicular to the horizontal plane.

31\. (New) The rotorcraft of The rotorcraft of
wherein the shock absorber tube comprises a closed end and an axially opposed open end, wherein the mounting arm is provided close to the closed end, and wherein the link fixation is provided close to the open end.

OFFICE 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 .
EXAMINER’S AMENDMENT
An examiner’s amendment to the record appears below. Should the changes and/or additions be unacceptable to applicant, an amendment may be filed as provided by 37 CFR 1.312. To ensure consideration of such an amendment, it MUST be submitted no later than the payment of the issue fee.
Authorization for this examiner’s amendment was given in an interview with Michael S. Brodbine on 8th January 2024.
The application has been amended as follows:
In claim 13 line 3, change “…comprises another link…” to “…comprises an other link…”.
In claim 25 line 19, change “…and the lateral longeron;…” to “…and the longeron;…”.
In claim 26 line 3, change “…comprises another link…” to “…comprises an other link…”.
In claim 30 line 1, change “… of claim 263,” to “…of claim 26,”.
REASONS FOR ALLOWANCE
Claims 12 and 25 are allowed.
The following is an examiner’s statement of reasons for allowance:
Brand et al. (US 2023/0278701) teaches a non-retractable wheel-type landing gear as explained in the non-final rejection mailed 23rd September 2024.
Sikorsky (US 2,843,345) teaches a main landing gear of a helicopter secured to the fuselage by linkages.
Nannoni et al. (US 2011/0147518) teaches landing gear having mounting means fitted to the fuselage.
However, it would not have been obvious to modify these references to arrive at the claimed invention without the use of impermissible hindsight. The attachment of a mounting arm of a landing gear to a first fitting mounted to a cabin floor and a lateral longeron, and arrangement of  link fixation at an angle in a range from 45 degrees to 120 degrees with respect to the mounting arm and its attachment to a second fitting is a novel concept.
Claims 13-24 are allowable due to dependency on claim 12.
Claims 26-31 are allowable due to dependency on claim 25.
Any comments considered necessary by applicant must be submitted no later than the payment of the issue fee and, to avoid processing delays, should preferably accompany the issue fee.  Such submissions should be clearly labeled “Comments on Statement of Reasons for Allowance.”
Conclusion

APPLICANT REBUTTAL: Remarks
Reconsideration of the above-identified application in view of the present Amendment is respectfully requested.
Claims 1-15 were pending in the application. By this paper, without acquiescing in the grounds for rejection and for expediting prosecution, claim 12 has been amended. Claims 1-11 have been cancelled, and new claims 16-31 have been added. No new matter has been added by the present amendment.
Claim Bases
Original claims 1-11 have been cancelled. Independent claim 12 has been amended in accordance with the Examiner's suggestion on page 2, paragraph 2, of the Non-Final Office Action. More specifically, the term "the at least one non-retractable wheel-type landing gear" was added to amended claim 12 for the purpose of clarity as suggested by the Examiner. Original claims 13-15 remain unchanged. Furthermore, new claims 16-24 have been added based on original claims 2, and 4-11, respectively, and new claims 25-31 have been added based on original claims 12, 13, 14-15, 16, 17, 18-19, and 20, respectively. Please note that no new matter has been added by the present amendment.
Claim Ob
j
ections
Claims 5, 6 and 12 were objected to because of certain informalities.
Without acquiescing in the Patent Office's grounds of objection, and solely for the purpose of expediting prosecution, claims 5 and 6 have been cancelled and claim 12 has been amended with the objections in mind and as suggested by the Examiner.
Accordingly, Applicant respectfully requests reconsideration and withdrawal of the objections to the claims.
Claim Rejections Under 35 U
.
S.C.
$
102 and 103 and Allowed Sub
j
ect Matte
r
Claims 1, 2 and 7 were rejected under 35 U.S.C. §102 as being anticipated by U.S. Publication No. 2023/0278701 to Brand, hereinafter Brand; and
claims 3-6 and 8-11 were rejected under 35 U.S.C. §103 as being obvious over Brand, as applied to claim 1 above, and further in view of U.S. Publication No. 2006/0237584 to Hinton, hereinafter Hinton.
Applicant respectfully traverses these rejections for at least the following reasons.
At the outset, Applicant notes the indication on page 9 of the Office Action of the allowance of claims 12-15. Applicant thanks the Patent Office for favorable review of these claims. Without acquiescing in the grounds for rejection, and for expediting prosecution Applicant has i) cancelled claims 1-11; ii) amended independent claim 12 to overcome the objection as suggested by the Examiner; and vi) added new claims 16-24 to depend from allowable claim 12.
Accordingly, independent claim 12 is allowed, as indicated on page 9 of the Office Action.
Claims 13-24 all depend either directly or indirectly from claim 12, and are therefore allowable for at least the same reasons as claim 12. Moreover, these claims add further limitations that also render them separately allowable.
Accordingly, Applicant respectfully requests withdrawal of the rejection of these claims.
New Claims
New claim 16-24 depends from allowed claim 12, and are therefore allowable for at least the same reasons as claim 12. Moreover, these claims add further limitations that also renders them separately allowable.
New claim 25 includes similar limitations as allowed independent claim 12 is and are therefore allowable for at least similar reasons as claim 12.
Claims 26-31 all depend either directly or indirectly from claim 25, and are therefore allowable for at least the same reasons as claim 25. Moreover, these claims add further limitations that also render them separately allowable.
Conclusion


CITED REFERENCE SUMMARIES: Ref US2843345A: [content unavailable]
Ref US20110147518A1: [content unavailable]
Ref US20230278701: Claims:
1. A landing wheel assembly for a rotorcraft having a light on gear phase during takeoff and landing, the landing wheel assembly comprising:
a tire including first and second side walls each having a vertical length, the tire forming a center aperture; and an anti-roll oscillation rim comprising: a center disc disposed in the aperture of the tire; a first side wall support plate protruding from the center disc and extending at least 25 percent of the vertical length of the first side wall of the tire; and a second side wall support plate protruding from the center disc and extending at least 25 percent of the vertical length of the second side wall of the tire; wherein, the first and second side wall support plates support the first and second side walls, respectively, to stiffen the tire in the light on gear phase of takeoff and landing, thereby reducing roll oscillations of the rotorcraft.
2. The landing wheel assembly as recited in claim 1 wherein the center disc comprises first and second center disc halves, the first side wall support plate protruding from the first center disc half and the second side wall support plate protruding from the second center disc half.
3. The landing wheel assembly as recited in claim 2 wherein the first center disc half is coupled to the second center disc half to sandwich the tire therebetween.
4. The landing wheel assembly as recited in claim 1 wherein the first and second side wall support plates are curved to contour the first and second side walls.
5. The landing wheel assembly as recited in claim 1 wherein the first and second side wall support plates comprise flat side wall support plates.
6. The landing wheel assembly as recited in claim 1 wherein the first and second side wall support plates are integral with the center disc.
7. The landing wheel assembly as recited in claim 1 wherein the first and second side wall support plates are separable from the center disc and coupled to the center disc with one or more fasteners.
8. The landing wheel assembly as recited in claim 7 wherein each first and second side wall support plate comprises a center interface portion, the center interface portion coupled to the center disc with the one or more fasteners.
9. The landing wheel assembly as recited in claim 7 wherein the anti-roll oscillation rim comprises a plurality of side wall support plates including the first and second side wall support plates, the side wall support plates interchangeably attachable to the center disc.
10. The landing wheel assembly as recited in claim 7 wherein the first and second side wall support plates are formed from a different material than the center disc.
11. The landing wheel assembly as recited in claim 10 wherein the first and second side wall support plates are formed from steel and the center disc is formed from aluminum.
12. The landing wheel assembly as recited in claim 1 wherein the first and second side wall support plates extend at least 50 percent of the vertical lengths of the first and second side walls of the tire, respectively.
13. The landing wheel assembly as recited in claim 1 wherein the first and second side wall support plates extend at least 75 percent of the vertical lengths of the first and second side walls of the tire, respectively.
14. The landing wheel assembly as recited in claim 1 wherein each first and second side wall has a surface area, the first side wall support plate covering at least 25 percent of the surface area of the first side wall and the second side wall support plate covering at least 25 percent of the surface area of the second side wall.
15. The landing wheel assembly as recited in claim 1 wherein the proximal end of each first and second side wall forms a bead; and
wherein, each first and second side wall support plate has a tire-facing surface forming a bead rest, the bead rests receiving the beads of the tire to secure the tire to the anti-roll oscillation rim.
16. The landing wheel assembly as recited in claim 15 wherein the bead rests are closer to the proximal ends of the first and second side wall support plates than the distal ends of the first and second side wall support plates.
17. A helicopter having a light on gear phase during takeoff and landing, the helicopter comprising:
a fuselage; and a landing gear system coupled to an underside of the fuselage, the landing gear system including port and starboard landing wheel assemblies, each landing wheel assembly comprising: a tire including inboard and outboard side walls each having a vertical length, the tire forming a center aperture; and an anti-roll oscillation rim comprising: a center disc disposed in the aperture of the tire; an inboard side wall support plate protruding from the center disc and extending at least 25 percent of the vertical length of the inboard side wall of the tire; and an outboard side wall support plate protruding from the center disc and extending at least 25 percent of the vertical length of the outboard side wall of the tire; wherein, the side wall support plates support the side walls to stiffen the tires in the light on gear phase of takeoff and landing, thereby reducing roll oscillations of the helicopter.
18. The helicopter as recited in claim 17 wherein the underside of the fuselage forms port and starboard wheel bays, the port and starboard landing wheel assemblies retractable into the port and starboard wheel bays, respectively.
19. The helicopter as recited in claim 17 wherein the side wall support plates are configured to increase a roll oscillation mode frequency of the helicopter in the light on gear phase of takeoff and landing.
20. The helicopter as recited in claim 17 wherein the side wall support plates reduce lateral flexibility of the tires in the light on gear phase of takeoff and landing.
Ref US20110147518: Claims:
1) A landing gear for an aircraft, comprising:
mounting means fitted to the fuselage of the aircraft; at least one wheel; and at least one supporting arm having a first end portion connected to said mounting means, and a second end portion opposite said first end portion, and to which said wheel is suspended; wherein said first end portion of said supporting arm comprises a seating portion fitted in rotary manner to a pin connected to said mounting means and extending crosswise to the supporting arm; and wherein an electrically controlled actuator is fitted to said seating portion, and is activated selectively to rotate said supporting arm, about said pin, between a first and second operating position defining a stowed in-flight configuration and a lowered landing configuration of the landing gear respectively; characterized in that said actuator projects, coaxially with said pin, from said seating portion of said supporting arm.
2) A landing gear as claimed in claim 1, characterized in that said actuator comprises a stator fitted to said pin; and a rotor radially more outwards than said stator and fixed to and projecting from said seating portion of said supporting arm.
3) A landing gear as claimed in claim 2, characterized in that said rotor defines a seat for housing said stator.
4) A landing gear as claimed in claim 1, characterized in that said supporting arm defines a shock-absorber comprising a cylindrical shaft, and a piston connected in axially-sliding manner to said shaft.
5) A landing gear as claimed in claim 4, characterized in that said shaft carries said first end portion of said supporting arm; and a portion of said piston projecting from said shaft defines said second end portion.
6) A landing gear as claimed in claim 4, characterized in that said pin is spaced apart from the axis of said shaft.
7) A landing gear as claimed in claim 1, characterized by comprising first locking means activated by an electric command to retain said supporting arm in said first operating position, and which are releasable in the absence of said electric command.
8) A landing gear as claimed in claim 7, characterized in that said first locking means comprise a first retaining member fitted to the fuselage of the aircraft; and a second retaining member fitted to said supporting arm, and which engages, said first retaining member when the supporting arm is in said first operating position; said first and second retaining member being designed to disengage by force of gravity in the absence of said electric command.
9) A landing gear as claimed in claim 8, characterized in that said first retaining member is U-shaped with its concavity facing downwards with reference to the grounded position of the aircraft; and in that said second retaining member comprises a projection on said supporting arm and which fits inside said first retaining member.
10) A landing gear as claimed in claim 7, characterized in that said electric command is activation of said actuator.
11) A landing gear as claimed in claim 1, characterized by comprising second locking means, which are clicked into place by movement of said supporting arm into said second operating position, and prevent release of the supporting arm from said second operating position.
12) A landing gear as claimed in claim 11, characterized in that said second locking means comprise a latch fitted to the fuselage of the aircraft and movable between a lock position, in which it engages a respective cooperating portion of said supporting arm, and a release position, in which it is detached from said cooperating portion; said latch being loaded elastically into said lock position, and being bounded by a ramp surface designed to allow movement of said supporting arm from said first to said second operating position, and by a retaining surface which defines a stop surface for said cooperating portion, to prevent release of said supporting arm from said second operating position.
13) A landing gear as claimed in claim 11, characterized by comprising electrically controlled third locking means for retaining said supporting arm in said second operating position.
14) A landing gear for an aircraft, comprising:
mounting means fitted to the fuselage of the aircraft; at least one wheel; and at least one supporting arm having a first end portion connected to said mounting means, and a second end portion opposite said first end portion, and to which said wheel is suspended; characterized by comprising a pin connected to said mounting means; and in that said supporting arm comprises a seating portion fitted about said pin, and which can be fitted, at the user's discretion, with a cover to define a fixed landing gear, or with an electrically controlled actuator activated selectively to rotate said supporting arm, about said pin, between a first and second operating position respectively defining a stowed in-flight configuration and a lowered landing configuration of a retractable landing gear.
Ref US2843345: Claims:
I claim:
1. Landing gear for rotary wing aircraft including a wheel and axle assembly, an extension extending from said axle at an angle of approximately 45 a supporting member in which said extension is journalled for rotation between two operative positions of said gear, one in which said axle is horizontal and another in which said axle is vertical, cooperating locking elements carried by said extension and said member and engageable to lock said assembly in either of said operative positions of said gear, means operatively connected to said extension for rotating said extension through 180 to move said assembly from one operative position to the other, cam means operatively connected to said locking elements for releasing said locking elements responsive to the initial rotative movement of said extension and resilient means operatively connected to said extension and said member and cocked by the releasing movement of said cam means for automatically re-engaging said locking elements at the end of said 180 movement of said extension.
2. Landing gear for rotary wing aircraft including a wheel and axle assembly, an extension extending from said axle at an angle of approximately 45 a supporting member in which said extension is axially movable and also rotatable between two operative positions of said gear, one in which said wheel is rotatable on said axle in vertical planes and the other in which said axle is downwardly directed and said wheel lies in horizontal planes, cooperating locking elements carried by said member and extension for locking said extension against rotation relative to said member in either of said operative positions of said assembly, means operatively'connected to said extension for moving said extension axially of said member to release said locking elements including a cam member carried by said supporting member, biasing means engaging said extension and urging the same axially in a direction to' engage said locking ele ments, and drive means coupled with said moving means for actuating said cam member to move said extension axially and release said locking elements and subsequently to rotate said axle assembly into its other operative position.
3. Landing gear for rotary wing aircraft including an oleo strut supported on said aircraft, a support at the lower end of said strut having a sleeve disposed at approximately 45 tothe vertical plane including the longitudinal axis of said strut, a normally horizontal wheel axle having a 45 extension journalled in said sleeve, a wheel journalled on said axle having a pneumatic bumper located at the extremity of said axle, means operatively connected to said extension for locking said extension to said sleeve in two angular positions of said extension relative to said sleeve, one in which said wheel axle is horizontal and another in which said axle is vertical and downwardly directed, said locking means being unlocked by axial movement of said extension, pilot operative means operatively connected to said extension for turning said extension through 180 relative to said sleeve to move said axle from either of said positions into the other position including a member mounted to rotate about the axis of said extension, and means included in said pilot operative means for moving said extension axially in said sleeve upon initial rotating movement of said member to unlock said extension.
4. Landing gear for rotary wing aircraft including a wheel and axle assembly, means operatively connected to said assembly for supporting said assembly in two ground engaging positions of said wheel, one in which said wheel lies in vertical planes and another in which it lies in horizontal planes, means operatively connected to said assembly for releasably locking said assembly in either of said positions, and means for automatically releasing said locking means and moving said assembly from either position into the other including a pinion gear rotatably mounted in said supporting means, a driven member for rotating said assembly, and a driving member driven by said pinion for rotating said driven member, said driving and driven members having cooperating cam faces operative to release said locking means upon initial movement of said driving member by said pinion.
5. A landing gear as claimed in claim 4 in which a spring is compressed by the initial unlocking movement of said driving member and urges said cam faces into registering position following movement of said assembly to re-engage said locking means.
6. A landing gear as claimed in claim 5 in which piston and cylinder elements are provided, one of which is movable, and a rack connected to the movable element is provided for driving said pinion.
7. Landing gear for rotary wing aircraft including a wheel and axle assembly, an extension extending from said axle at an angle of approximately 45, a supporting member in which said extension is journalled for rotation between two operative positions of said wheel and axle, one in which said axle is horizontal and another in which said axle is vertical, cooperating locking elements carried by said extension and said member and engageable to lock said Wheel and axle in either of said operative positions of said gear, means operatively connected to said extension for rotating said extension through 180 to move said wheel and axle from one operative position to the other, and cam means operably connected to one of said locking elements for releasing said locking elements responsive to the initial movement of said rotating means.
8. Landing gear for rotary wing aircraft including an oleo strut, means for mounting a wheel at the lower end of said strut comprising an oblique bearing, an axle assembly including a normally horizontal axle having an oblique extension journalled in said bearing, a wheel having a peripheral pneumatic tire and a pneumatic bumper mounted at the end of said axle, said Wheel being journalled on said axle, and means operatively connected to said axle assembly for moving said axle assembly between two operative positions, one in which said axle is horizontal and another in which said axle is downwardly directed.
9. Landing gear for rotary wing aircraft including a wheel and a wheel axle, said wheel having a landing surface engaging periphery and a landing surface engaging side, an extension extending from said axle at an angle of approximately 45, a supporting member in which said extension is journalled for rotation about an axis, and means operatively connected to said extension for rotating said extension and said Wheel between alternate positions in which the periphery and side respectively of said wheel are adapted for engagement with a landing surface.
l0. Landing gear for rotary wing aircraft including a wheel and a wheel axle, said wheel having a landing surface engaging periphery and a landing surface engaging side, an extension extending from said axle at an angle of approximately 45, a supporting member in which said extension is journalled for rotation about an axis, means operatively connected to said extension for rotating said extension and said wheel between alternate positions in which the said periphery and side respectively of said wheel are adapted for engagement with a landing surface, and means operatively connected to said wheel for locking said wheel in each of its alternate positions.
11. Landing gear for rotary wing aircraft including a wheel and a wheel axle, said wheel having a landing surface engaging periphery and a landing surface engaging side, an extension extending from said axle at an angle of approximately 45", a supporting member in which said extension is journalled for rotation about an axis, means operatively connected to said extension for rotating said extension and said wheel between alternate positions in which the said periphery and side respectively of said wheel are adapted for engagement with a landing surface, and means for locking said wheel in each of its alternate positions including a cooperating notch and lug operatively connected between said extension and said supporting member.
12. Landing gear for rotary wing aircraft including a wheel and a wheel axle, said wheel having a landing surface engaging periphery and a landing surface engaging side, an extension extending from said axle at an angle of approximately 45, a supporting member in which said extension is journalled for rotation about an axis, means operatively connected to said extension for rotating said extension and said wheel between alternate positions in which the said periphery and side respectively of said wheel are adapted for engagement with a landing surface, means for locking said wheel in each of its alternate positions including a cooperating notch and lug operatively connected between said extension and said supporting member, and means operatively connected to said extension for moving said extension axially to disengage said notch and lug.
References Ci
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