Manufacturer North American Aviation
Aircraft P-51 Mustang
Part Number 73-33578-3
Rod End Manufacturer P/N ATE-6N (Schafer)
Proper Description ROD ASSEM – LANDING GEAR RETRACTING STRUT CONNECTING
Location One assembly is located in each main landing gear wheel well
Nickname Gear Links / Landing Gear Rod Ends
AC.A. 01-151-L1, Landing Gear Retraction Rod End Failures & Safety Spring Installation, 31-Oct-2018
Nobody wants to witness or participate in a gear up landing in a Mustang. It can easily be a $1,000,000 repair. And while the most common reason a Mustang ends up on its belly is pilot error, another culprit can be the failure of the landing gear rod end. Fortunately, there are preventative measures and fixes that almost eliminate the likelihood of this failure mode. However, even if an aircraft has been modified, it doesn’t totally eliminate the chance of a rod end failure. AirCorps Aviation in Bemidji MN has compiled a comprehensive explanation of the hardware and failure modes of this critical component, with the belief that it is something every pilot and mechanic involved with a Mustang should thoroughly understand. Most importantly if you extend the gear on a Mustang and don’t get a green light, DON’T recycle the gear. Read on to learn why…
The P-51 Mustang ROD ASSEM – LANDING GEAR RETRACTING STRUT CONNECTING (P/N – 73-33578-3), is located in each landing gear wheel well, between Station 50 and Station 75 of the wing.1
1For purposes of length, we will refer to this assembly as installed on a P-51D per Equipment Installation – Landing Gear Wing (P/N 106-33014).
The 73-33578-3 assembly consists of a .625 OD x .120 wall Chrome Moly steel tube that is threaded on both ends to accept two ATE-6N Rod Ends and attaching hardware. Each end is drilled with a clevis pin inserted to secure the rod ends along with a lock washer and nut. It is also vertically drilled and tapped to mount a special bolt that contacts the landing gear down position indicator switch.
The complete rod assembly component can be simply described as providing two major functions:
Because the hydraulic strut never fully bottoms in either direction, the rod assembly is constantly under pressure or tension at both ends of travel. Because of the hinge-like motion of the cycle, misalignment of the bearings will cause additional pressure and tension, and potentially failure of the rod ends.
The landing gear installation embodies a retractable main gear assembly in each wing panel and a retractable tail gear assembly in the fuselage, each assembly being completely enclosed in the retracted position. All shock struts employ the air-oil combination for cushioning. The positioning of all three landing gear assemblies is controlled simultaneously by one lever on the lower left side of the cockpit.
The 73-33578 ROD ASSEM – LANDING GEAR RETRACTING STRUT CONNECTING was originally designed and engineered by North American on April 22, 1941. This design was used on the P-51A, A-36, through the P-51D, including the experimental and lightweight mustang subtypes.
In May 1942 the revised design, P/N 73-33578-3, was drafted for production. This new rod end assembly was indicated by the addition of a the -3 to the part number. Improvements on this rod end assembly from the initial 73-33578 design include the following:
The original 73-33578 drawing also indicates that the completed assembly is to be finished per army spec FS-21 indicating cadmium plating to prevent corrosion.
While the 73-33578 and 73-33578-3 are interchangeable, we do not suggest doing so as design improvements were made and prior production lots were deemed inactive for future use.
Use the instructions for landing gear maintenance outlined in Tech Order – T.O. No. 1F-51D-2 (AN 01-60JE-2), Maintenance Instructions for F-51D, F-51M, ZF-51K, and TF-51D, 30-Nov-1956
This heavily worked and integral component on the P-51 Mustang requires frequent inspection and attention to prevent failure, particularly if operating 70+ year old rod ends.
Some key questions in determining if your 73- 33578 rod assemblies need to be inspected / tested / replaced / repaired:
AirCorps recommends these additional inspections / actions.
As a reference, the Aircraft Inspection & Maintenance Guide – P-51, 00-20A-2-P-51, 7-Nov-1947 outlines a detailed inspection of the landing gear system that should happen during pre-flight, after flight, daily, and at 25, 50, 100 hour inspections.
The difference between the often referred to light or heavy rod end can be seen in the transition from the threaded end to the rod end assembly. The early or “light” version of the ATE-6N had a narrower neck in which the diameter reduced in size.
A number of operators have experienced broken rod ends as the result of using lightweight variants. If the rod end on the cylinder end of the rod breaks, the rod will fall and jam on the Sta. 61.5 wing rib. When an extension occurs after the rod breaks the landing gear will extend halfway and stop. With a rod jammed on the rib and a broken rod, the only option will be a gear up landing.
On the right we provide photos to show a lightweight version and a heavy version of the ATE-6N.
How to inspect – visual inspection, magnaflux
Tolerance of damage or wear : Zero
Solutions offered: Replacement of Rod Ends
As the images above show, this end appears to have been rolled off – meaning the force applied to retract the gear has bent the rod end until failure.
With the landing gear retracted, a failure at the cylinder end of 73- 33578 Rod Assembly causes the broken rod to fall and wedge on the structural skin of the aircraft and rib at wing station 61.5. If the rod breaks and wedges on the rib, there is nothing a pilot can do to solve the problem in the air.
The rendering below simulates a broken retract rod with the landing gear upper cylinder in the up position indicated in red. The broken rod assembly, separated at the extended cylinder end is colored blue. The majority of the 73-33578 rod assembly will remain attached to the Arm Landing Gear Torque (Nicknamed the Porkchop). The rod assembly will wedge itself between the heavy skin and rib at wing station 61.5 and will prevent the landing gear from fulling extending.
When a failure of either rod end occurs at initial retraction, the pilot will typically observe a brief indication of “Gear Up” followed by a indication of “Gear Unsafe”. This is due to the rod releasing the gear position switch in contact with the plunger located on the retract rod after the rod falls from position. If the rod does not jam, the gear will fully extend and a normal landing can be made. As you will not have a safe indication, cycling the gear may present itself as an option. DO NOT CYCLE THE GEAR, this will not solve the issue and will only open the possibility of further jamming in the landing gear system! The landing gear system relies on timing and position of several components and it is high likely more damage will occur.
When a failure occurs in extension, during landing phase of flight, again the pilot will typically observe a “Gear Extended” indication immediately followed by an unsafe light. Typically if an extended indication followed by unsafe indication is observed the landing gear has extended and locked down. Like the failure in retraction, the rod has become misplaced and will no longer contact the rod position switch. Again, DO NOT CYCLE THE GEAR. Have a spotter observe the extension of the gear.
Pilot’s extending the landing gear and not getting a green gear down light should not recycle the gear. In any situation, regardless of the integrity of the landing gear normal or failed, the pilot should never recycle their landing gear without completing a full cycle. The pilot may decide to do this due to an indication or deviation in intent of flight. The system must always fully complete a cycle before a direction change is made.
If you put gear down and then quickly cycle the gear before letting the complete system cycle, you run the risk of putting the door and landing gear timing system out of sequence & possibly preventing extension of the gear. On the down cycle, the gear drop with no timing of the doors. On the upcycle of landing gear both timing and sequencing is occuring.
This out of sequence failure mode has the potential to prevent extension of the gear and can also disturb airflow to the radiator and oil cooler due to open doors disturbing the airflow. Radio call the tower, someone on the ground, or a wing man for confirmation of landing gear position.
As a preventative measure and safety enhancement, AirCorps recommends the installation of a spring between the retract rod and the extrusion in the gear well on the inboard (cylinder) side of the rod assembly.
Installing Broken Rod End Retract Spring
(2) Spring – MS24586
(2) AN742D10 or MS21919DG10 Adel Clamp
(4) AN365-1032A Nuts
Work performed between station 50 & station 61.5 of wing assembly
If you’re replacing 73-33578 ROD ASSEM – LANDING GEAR RETRACTING STRUT CONNECTING, ensure airworthiness prior to purchasing by inspecting for cracks, straightness, and finish. If swapping out ATE-6N rod ends, operators and maintainers should confirm them to be the heavier variant. AirCorps is available to perform inspections, answer questions, complete services related to overhaul of landing gear, system components, along with services related to installation.
ATE-6N – Heavy Rod Ends are available for purchase on www.AirCorpsDepot.com
WHILE AIRCORPS (VENDOR) BELIEVES THAT THE INFORMATION CONTAINED THEREIN IS ACCURATE AND CORRECT, VENDOR DOES NOT WARRANT THE ACCURACY OR THE CORRECTNESS OF ANY DRAWINGS, MANUALS, OR THE INFORMATION CONTAINED THEREIN. THE INFORMATION, DRAWINGS AND REFERENCE MATERIAL ARE SUPPLIED TO THE CUSTOMER ON AN “AS IS” BASIS WITHOUT ANY WARRANTIES, EXPRESS OR IMPLIED, INCLUDING, BUT NOT LIMITED TO, ANY WARRANTIES OF MERCHANTABILITY OR FITNESS FOR ANY PARTICULAR PURPOSE. ALL WORK SHOULD BE COMPLETED IN ACCORDANCE WITH FAA REGULATIONS AND APPROVED DATA.