AD 96-07-03

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AD Number:
96-07-03
Document Type:
AD Final Rules
Docket Number:
95-SW-04-AD
Subject Heading:
Airworthiness Directives; Societe Nationale Industrielle Aerospatiale and Eurocopter France Model AS...Show more
Subject:
Cyclic Pitch Change Control Rod
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
03/28/1996
Effective Date:
05/02/1996
Make:
Airbus Helicopters
Model:
AS355E | AS355F | AS355F1 | AS355F2 | AS355N | AS350B | AS350B1 | AS350B2 | AS350BA | AS350D
Product Type:
Aircraft
Product Subtype:
Rotorcraft
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
AIR-700: Compliance & Airworthiness Division
Office of Primary Responsibility:
AIR-730: International Validation Branch
CFR Part Reference:
Part 39 (61 FR 13655 NO. 61 03/28/96)
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 96-07-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   95-SW-04-AD

AMENDMENT:   39-9552

AD NUMBER:   96-07-03

SUBJECT HEADING:   Airworthiness Directives; Societe Nationale Industrielle Aerospatiale and Eurocopter France Model AS 350B, BA, B1, B2, and D, and Model AS 355E, F, F1, F2, and N Helicopters

ACTION:   Final rule

SUMMARY:   This amendment adopts a new airworthiness directive (AD), applicable to Societe Nationale Industrielle Aerospatiale and Eurocopter France (Eurocopter France) Model AS 350B, BA, B1, B2, and D, and Model AS 355E, F, F1, F2, and N helicopters, without an autopilot installed, that requires a visual inspection to determine whether the cyclic pitch change control rod (rod) end fittings were safetied, and removal and replacement of the rod if the rod end fittings were not safetied. This amendment is prompted by a manufacturer's report that some of the rod end fittings had not been safetied at the factory. The actions specified by this AD are intended to prevent loss of tightening torque on the adjustment nuts of the rod, shifting of the neutral point of the cyclic stick, reduction in the amount of available movement of the cyclic stick in the roll axis, and subsequent reduction in the controllability of the helicopter.

DATES:   EFFECTIVE DATE: Effective May 2, 1996.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:   Mr. Richard Monschke, Aerospace Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5116, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION:  
A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to Eurocopter France Model AS 350B, BA, B1, B2, and D, and Model AS 355E, F, F1, F2, and N helicopters, without an autopilot installed, was published in the Federal Register on November 1, 1995 (60 FR 55491). That action proposed to require a visual inspection to confirm that the rod end fittings are safetied, and removal and replacement of the rod, if necessary.

Eurocopter France has issued Eurocopter Service Bulletin No. 01.38, dated June 26, 1994, for the Model AS 355 series helicopters, and Eurocopter Service Bulletin No. 01.42, dated June 28, 1994, for the Model AS 350 series helicopters, which specifies a visual inspection to determine whether the rod end fittings have been safetied; reinstallation of the forward lower fairing if the rod end fittings have been safetied, and removal and replacement of the rod with an airworthy rod and reinstallation of the forward lower fairing if the rod end fittings have not been safetied. The Direction Generale De L'Aviation Civile, which is the airworthiness authority for France, classified this service bulletin as mandatory and issued AD 94-179-051(B) and AD 94-180-069(B), both dated August 3, 1994, in order to assure the continued airworthiness of these helicopters in France.

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposal or the FAA's determination of the cost to the public. However, a note has been inserted at the end of paragraph (c) to alert the reader that a Eurocopter Service Bulletin has been issued that pertains to the requirements of this AD. The FAA has determined that air safety and the public interest require the adoption of the rule with the noted change.

The FAA estimates that 498 helicopters of U.S. registry will be affected by this AD, that it will take approximately one-fourth of a work hour per helicopter to inspect the rod end fittings, and 1 work hour to remove and reinstall the rod, if necessary, and that the average labor rate is $60 per work hour. Required parts will be provided by the manufacturer. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $37,350.

The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this action (1) is not a " significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES."

List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39 - AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 USC 106(g), 40113, 44701.

§ 39.13 - [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive to read as follows:

REGULATORY TEXT:  
96-07-03 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE AND EUROCOPTER FRANCE: Amendment 39-9552. Docket No. 95-SW-04-AD.

Applicability: Model AS 350B, BA, B1, B2, and D, and Model AS 355E, F, F1, F2, and N helicopters, with cyclic pitch change control rod, part number (P/N) 704A34-113-279, installed, and without an autopilot installed, certificated in any category.

NOTE 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (d) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD.

Compliance: Required as indicated, unless accomplished previously.

To prevent loss of tightening torque on the adjustment nuts of the cyclic pitch change control rod, shifting of the neutral position of the cyclic stick, reduction in the amount of available movement of the cyclic stick in the roll axis, and subsequent reduction in the controllability of the helicopter, accomplish the following:

(a) Within 100 hours time-in-service (TIS) after the effective date of this AD, remove the forward lower fairing and visually inspect the cyclic pitch change control rod (rod), P/N 704A34-113-279, to determine whether the end fittings have been safetied (see Figure 1, Detail 1, tabs bent around the adjustment nut).

(b) If the visual inspection indicates that the rod end fittings have been safetied, reinstall the forward lower fairing.

(c) If the visual inspection indicates that the rod end fittings have not been safetied (see Figure 1, Detail 2, tabs not bent around the adjustment nut), accomplish the following in accordance with the applicable maintenance manual:

(1) Immobilize the cyclic control.

(2) Remove the rod and replace it with an airworthy rod on which the rod end fittings have been safetied.

(3) Reinstall the forward lower fairing.

(4) Verify proper operation of the cyclic control.

NOTE 2: Eurocopter Service Bulletin No. 01.38, dated June 26, 1994, for the Model AS 355 series helicopters, and Eurocopter Service Bulletin No. 01.42, dated June 28, 1994, for the Model AS 350 series helicopters, pertain to this subject.

(d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used when approved by the Manager, Rotorcraft Standards Staff, FAA, Rotorcraft Directorate. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Standards Staff.

NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff.

(e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the helicopter to a location where the requirements of this AD can be accomplished.

(f) This amendment becomes effective on May 2, 1996.





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