AD 88-08-01

AD Final Rules - DRS_88-08-01.html
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AD Number:
88-08-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; (BELL); HERCULES; LENAIR CORPORATION; SMITH HELICOPTERS; AND WEST COAST ...Show more
Subject:
Rod End Bearing Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/06/1988
Make:
Bell Helicopter Textron, Inc. | Rotorcraft Development Corporation | Smith Helicopters | West Coast Fabrications
Model:
TH-1L | UH-1E | UH-1L
Product Type:
Aircraft
Product Subtype:
Rotorcraft
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 88-08-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5887

AD NUMBER:   88-08-01

SUBJECT HEADING:   Airworthiness Directives; (BELL); HERCULES; LENAIR CORPORATION; SMITH HELICOPTERS; AND
WEST COAST FABRICATIONS Model UH-1E, UH-1L, and TH-1L Helicopters

ACTION:  

SUMMARY:  

DATES:   Effective May 6, 1988.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
88-08-01 (BELL); HERCULES; LENAIR CORPORATION; SMITH HELICOPTERS; AND WEST COAST FABRICATIONS: Amendment 39-5887. Applies to Model UH-1E, UH-1L, and TH-1L helicopters certified by Hercules; Lenair Corporation; Smith Helicopters, and West Coast Fabrications certified in any category that have P/N 204-076-428-1, -3, or -5 rod end bearing assemblies installed.

Compliance is required as indicated, unless already accomplished.

To detect possible cracks in the collective and cyclic rod end bearing assemblies, P/N 204-076-428-1, -3, or -5, installed on Model UH-1E, UH-1L, and TH-1L helicopters, accomplish the following:

(a) Prior to the next flight after the effective date of this AD and thereafter at intervals not to exceed 10 hours' time in service from the last inspection, visually inspect the rod end bearing assemblies for cracks. Perform the visual inspections by disconnecting the cyclic and collective control tube assemblies from the swashplate horns and the collective pitch control lever.

(b) Whenever the rod end bearing assemblies are removed for any reason, inspect for cracks using a fluorescent penetrant or equivalent method.

NOTE: Inspections specified by paragraphs (a) and (b) above are not required on rod end bearing assembly P/N 204-076-428-5 having documented time in service of less than 600 hours.

(c) If a crack is found during these inspections replace the rod end bearing with a serviceable part prior to further flight.

(d) Replace rod end bearing assemblies, P/N 204-076-428-1 or -3 within 11 calendar months from the effective date of this AD with rod end bearing assembly, P/N 204-076-428-5, having a documented known service life of less than 600 hours' time in service.

(e) Replace rod end bearing assembly P/N 204-076-428-5, not having a documented known service life, or those with greater than 600 hours' time in service, within 11 calendar months from the effective date of this AD with rod end bearing assembly P/N 204-076-428-5 having a documented service life of less than 600 hours' time in service.

(f) Retire from service rod end bearing assembly, P/N 204-076-428-5 at 600 hours' time in service or less after initial replacement described in paragraphs (d) and (e).

(g) An equivalent method of compliance which provides an equivalent level of safety with this AD may be used when approved by the Manager, Helicopter Certification Branch, Federal Aviation Administration, Fort Worth, Texas, 76193-0170.

This amendment, 39-5887, becomes effective May 6, 1988.

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