AD 68-04-04 R2

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AD Number:
68-04-04 R2
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BRANTLY Models B-2, B-2A, and B-2B Helicopters
Subject:
Tail Rotor Blade
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/14/1983
Make:
Brantly International, Inc.
Model:
B-2 | B-2A | B-2B
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Superseded AD: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Superseded By: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:
AIRWORTHINESS DIRECTIVES FINAL RULES: 68-04-04 R2
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4552

AD NUMBER:   68-04-04 R2

SUBJECT HEADING:   Airworthiness Directives; BRANTLY Models B-2, B-2A, and B-2B Helicopters

ACTION:  

SUMMARY:  

DATES:   Effective February 14, 1983.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
68-04-04 R2 BRANTLY: Amendment 39-557 as amended by Amendment 39-3568 is further amended by Amendment 39-4552. Applies to Model B-2, B-2A, and B-2B helicopters, certificated in all categories.

For tail rotor blades, P/N 111-11, with 100 or more hours' time in service after February 27, 1968, compliance required prior to further flight, unless already accomplished, and, thereafter, at intervals not to exceed 100 hours' time in service from the last inspection. For tail rotor blades, P/N 111-11A, with 300 or more hours' time in service after August 15, 1979, compliance required prior to further flight, unless already accomplished, and, thereafter, at intervals not to exceed 300 hours' time in service from the last inspection.

To prevent failures of the tail rotor blade at the spar retention areas, accomplish the following:

(a) Remove, clean, and mark the tail rotor blades in accordance with Brantly Service Bulletin, SB No. B2B-68-1, dated February 14, 1968, and accomplish the following inspections:

(1) Visually inspect the inside and outside of the spars of the tail rotor blades particularly at the inside bearing boss radius for evidence of pitting corrosion. If corrosion is detected, replace the blade assembly before further flight with an airworthy part.

(2) Inspect the inside and outside of the spars of the tail rotor blades particularly at the inside bearing boss radius for evidence of cracks using dye penetrant procedures as indicated in Figure 1 of Brantly Service Bulletin, SB No. B2B-68-1, dated February 14, 1968, or use an equivalent method approved by the Manager, Aircraft Certification Division, FAA, Southwest Region, Fort Worth, Texas 76101. If a crack is detected, replace the blade assembly before further flight with an airworthy part.

(b) After the tail rotor blades have been inspected or replaced with an airworthy part as provided in paragraphs (a)(1) and (a)(2) of this Airworthiness Directive, assemble them in accordance with Brantly Service Bulletin, SB No. B2B-68-1, dated February 14, 1968.

(c) To prevent confusion during subsequent inspections of tail rotor blades due to similarity between tail rotor blade assembly, PN 111-11, and assembly, PN 111-11A, use a permanent marking ink or equivalent acceptable for aluminum aircraft components to mark the tail rotor blade assembly with the proper part number identification (see Fig. 1 for dimensions that determine the part configuration).

(d) In order to facilitate inspection of the tail rotor blade spar retention area, do not repaint the spar retention area.

(e) The requirements of paragraphs (c) and (d) above must be implemented no later than the next compliance with paragraph (a) of this AD after February 14, 1983.

Amendment 39-557 became effective February 27, 1968, to all persons except those to whom it was made effective on receipt of airmail letter dated February 14, 1968.

Amendment 39-3568 became effective October 28, 1979.

This Amendment 39-4552 becomes effective February 14, 1983.




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