AD 79-04-03 R2

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AD Number:
79-04-03 R2
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Empresa Brasileira De Aeronautica, S.A. (Embraer) Models EMB-110P1 and EMB-110P2
Subject:
Landing Gear
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/07/1983
Make:
Embraer S.A.
Model:
EMB-110P1 | EMB-110P2
Product Type:
Aircraft
Product Subtype:
Small/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Superseded AD: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Superseded By: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: 79-04-03 R2
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4557

AD NUMBER:   79-04-03 R2

SUBJECT HEADING:   Airworthiness Directives; Empresa Brasileira De Aeronautica, S.A. (Embraer) Models EMB-110P1 and EMB-110P2

ACTION:  

SUMMARY:  

DATES:   Effective February 7, 1983.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
79-04-03 R2 EMPRESA BRASILEIRA DE AERONAUTICA, S.A. (EMBRAER): Amendment 39-3411 as amended by Amendment 39-3623 is further amended by Amendment 39-4557. Applies to Models EMB-110P1 and EMB-110P2 (all serial numbers) airplanes certificated in any category.

COMPLIANCE: Required as indicated unless already accomplished.

To preclude failure of the oleo strut assemblies, accomplish the following as indicated below.

1. Inspect and replace oleo strut assemblies (P/N 15164A, B, or C, and 15165A, B, or C), on shock struts (P/N 14570 and 14575) which have 2,000 landings or more in accordance with the following:

a. Prior to the first flight of each day, using a 10-power magnifying glass, conduct a visual inspection of the shock struts of the main landing gear at the weld that joins the torque link-to-shock strut attachment. If cracks are found, prior to further flight, replace the component with a serviceable part.

b. Within the next 200 landings and each 200 landings thereafter, using a dye-penetrant method, per the Accomplishment Instructions in Embraer Service Bulletin 110-32- 018 dated June 8, 1978, inspect the area outlined in 1.a. above. If cracks are found, prior to further flight, replace the component with a serviceable part.

c. Retire from service shock struts (P/N 14570 and 14575) which have 3,000 landings or more.
2. Inspect and replace upper half-drag struts (P/N 14284 and 14334) without shot- peening treatment in accordance with the following:

a. Prior to the first flight of each day, using a 10-power magnifying glass, conduct a visual inspection of the external side of the upper region of the half-drag strut, near the hydraulic actuator joint. If cracks are found prior to further flight, replace the component.

b. Prior to further flight, unless already accomplished within the previous 200 landings, and each 200 landings thereafter, using a dye-penetrant method, per the Accomplishment Instructions in Embraer Service Bulletin 110-32-018 dated June 8, 1978, inspect the external and internal side of the half-drag strut (P/N 14284 and 14334). If cracks are found, prior to further flight, replace the failed component.

c. Within the next 100 landings after the effective date of this revision, replace any half-drag struts that have logged 18,750 landings or more.

3. Unless accomplished within the last 400 landings, inspect and replace upper half- drag strut (P/N 14284A and 14334A) which have shot-peening treatment in accordance with the following:

a. For components with 9,700 landings or more on the effective date of this AD, prior to further flight, and at each 400 landings thereafter, comply with paragraph 3.c. of this AD.

b. For components with less than 9,700 landings on the effective date of this AD, comply with paragraph 3.c. of this AD before the accumulation of 9,700 landings and at each 400 landings thereafter.

c. Inspect the external and internal side of the half-drag strut using a dye- penetrant method, per the Accomplishment Instructions in Embraer Service Bulletin 110-32-018 dated June 8, 1978. If cracks are found, prior to further flight, replace the failed component.

d. Within the next 100 landings after the effective date of this revision, replace any half-drag struts that have logged 18,750 landings or more.

4. On components on which landings are not recorded, one landing per flying hour may be used to determine the number of landings.

5. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Manager, Atlanta Aircraft Certification Office, FAA, 1075 Inner Loop Road, College Park, Georgia 30337, may adjust the inspection compliance times specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator.

6. Airplanes on which cracks are found may be flown to a base for replacement of the failed components in accordance with FAR 21.197.

7. Compliance with the provisions of this AD may be accomplished in an equivalent manner, when approved by the Manager, Atlanta Aircraft Certification Office, FAA, 1075 Inner Loop Road, College Park, Georgia 30337.

EMBRAER Service Bulletin No. 110-32-018 pertains to the subject matter of this AD.

Amendment 39-3411 became effective February 16, 1979.
Amendment 39-3623 became effective November 28, 1979.
This Amendment 39-4557 becomes effective February 7, 1983.

FOOTER: