TB 1-1670-260-12
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* Wipe blade with cheesecloth, NSN 8305-00-205-3558. Cloth snagging indicates possible crack.
3.2.3.1 Recovery of Damaged OH-58A/C and D Model Helicopters may further
compromise the structural integrity of the victim helicopter. The damaged helicopter
may not be approved for return to flight status without additional engineering evaluation
and possible depot level inspections. Post recovery personnel should visually identify
the areas of damage, record recovery flight data, and contact AMSAM-RD-AE-I-D-O
(Mr. Gerald Johnson Jr.) for corrective action to return the recovered helicopter to flight
status or for deposition of the recovered damaged helicopter.
References: A. Engineering Analysis of the OH-58DUnit Maintenance Aerial Recovery
Kit (UMARK) By Bell Helicopter Textron Inc (BHTI), Contract DAAH 10-00-C-
0055, dated 16 April 2001.
3.3.1 The UH-60 SERIES supplemental data compliments Chapter 6 of the UMARK
TM and provides the following recommendations prior to aircraft recovery operations
utilizing the UMARK. The intent is to ensure that all limitations described in reference A
analysis are incorporated for recovery operations.
3.3.2 Additional emphasis/wording is required in Work Packages 0022, 0023, and
0024. The following emphasis/wording is underlined and bolded to preclude damage to
the inboard damper brackets and supplements paragraph 7 b.:
3.3.2.1 Position mid-point of green/white sling (1), View A, under 2 o'clock position
main rotor blade retention assembly inboard of dampener bracket and as close to
main rotor mast as possible. (View C)
3.3.2.2 Position mid-point of green/white sling (2), View A, under 4 o'clock position
main rotor blade retention assembly inboard of dampener bracket and as close to
main rotor mast as possible. (View C)
3.3.2.3 Position midpoint of green/white sling (3), View A, under 8 o'clock position
main rotor blade retention assembly inboard of dampener bracket and as close to
main rotor mast as possible. (View C)
3.3.2.4 Position midpoint of green/white sling (4), View A, under 10 o'clock position
main rotor blade retention assembly inboard of dampener bracket and as close to
main rotor mast as possible. (View C)
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