AD 76-15-05

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AD Number:
76-15-05
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; CANADAIR Models CL-44D4 and CL-44J Airplanes
Subject:
Nose Landing Gear Bolts
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/17/1978
Make:
Bombardier Inc.
Model:
CL-44D4 | CL-44J
Product Type:
Aircraft
Product Subtype:
Large Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 76-15-05
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3181

AD NUMBER:   76-15-05

SUBJECT HEADING:   Airworthiness Directives; CANADAIR Models CL-44D4 and CL-44J Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 17, 1978.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
76-15-05 CANADAIR: Amendment 39-2676 as amended by Amendment 39-3181. Applies to all CL-44D4 and CL-44J airplanes, certificated in all categories.

Compliance required as indicated unless already accomplished.

Affects the nose landing gear retraction actuator lever attachment bolts.

(a) On airplanes with nose landing gear retraction actuator lever attachment bolts, P/N 44-85279, installed:

(1) Within the next 250 landings after the effective date of this AD, accomplish the following:

(i) Replace bolts with unused vacuum cadmium plated Voi-Shan bolts, P/N V.S.2738, or equivalent bolts. Voi-Shan bolts are identified by part number impression on the bolt head.

(ii) Install V.S.2738 bolts in accordance with paragraph 4.1(e) through 4.1(h) of Canadair Service Information Circular No. 387-CL44, Issue 2, (SIC) or an equivalent installation.

(b) On airplanes with V.S.2738 bolts installed:

(1) Within the next 25 landings after the effective date of this airworthiness directive, accomplish the following:

(i) Inspect V.S.2738 bolts in accordance with paragraph 4.1(a) through 4.1(c) of the SIC, or an equivalent inspection, for cracks, corrosion, pitting, or rework by chrome plating.

(ii) Replace bolts showing signs of any of the above defects, before further flight, with unused V.S.2738 bolts, and install in accordance with paragraph 4.1(c) thru 4.1(h) of the SIC or approved equivalent procedure.

(2) Vacuum cadmium plated V.S.2738 bolts, found free from defects, may be reinstalled provided:

(i) Within the next 500 hours in service or 125 landings, whichever occurs first, after reinstallation and thereafter, at intervals not to exceed 500 hours in service or 125 landings from the last inspection, the bolts are inspected for cracks by magnetic particle inspection or eddy current inspection or an equivalent procedure.

(ii) Reinstalled bolts that have attained 5000 hours in service or 1250 landings, must be replaced with unused V.S.2738 bolts or equivalent bolts, and installed in accordance with paragraph 4.1(c) thru 4.1(h) of the SIC or approved equivalent procedure.

(iii) The repetitive inspection required by paragraph (b)(2)(i) may be discontinued when the used bolts are replaced with unused vacuum cadmium plated V.S.2738 bolts or equivalent bolts and installed in accordance with paragraph 4.1(c) thru 4.1(h) of the SIC, or approved equivalent procedure.

(c) Unused vacuum cadmium plated Voi-Shan bolts, installed in accordance with paragraph (a)(1)(ii), must be replaced with unused bolts of the same type and installed in the same manner, at or before 13,500 hours in service or eight years, whichever occurs first. If bolts are removed prior to the aforementioned life limits, they must be inspected and installed in accordance with paragraph (b)(1)(i) and (ii).

(d) Equivalent inspections, installations, bolts, and service information circular revisions, must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.

(e) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the compliance time specified in this AD.

Amendment 39-2676 was effective July 28, 1976.

This amendment 39-3181 is effective April 17, 1978.

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