98-31589. Airworthiness Directives; Eurocopter France Model AS-365N2, SA- 360C, SA-365C, C1, C2, N, N1, and SA-366G1 Helicopters  

  • [Federal Register Volume 63, Number 228 (Friday, November 27, 1998)]
    [Rules and Regulations]
    [Pages 65548-65552]
    From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
    [FR Doc No: 98-31589]
    
    
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    DEPARTMENT OF TRANSPORTATION
    
    Federal Aviation Administration
    
    14 CFR Part 39
    
    [Docket No. 98-SW-05-AD; Amendment 39-10918; AD 98-24-32]
    RIN 2120-AA64
    
    
    Airworthiness Directives; Eurocopter France Model AS-365N2, SA-
    360C, SA-365C, C1, C2, N, N1, and SA-366G1 Helicopters
    
    AGENCY: Federal Aviation Administration, DOT.
    
    ACTION: Final rule; request for comments.
    
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    SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
    is applicable to Eurocopter France Model AS-365N2, SA-360C, SA-365C, 
    C1, C2, N, N1, and SA-366G1 helicopters. This action requires 
    inspecting for broken or out-of-tolerance attachment springs on the 
    tail rotor hub fairing (fairing), replacing broken attachment springs 
    and attachment springs that are out-of-tolerance, and marking the 
    fairing to indicate compliance with this AD. This amendment is prompted 
    by three in-service reports of failed attachment springs. The actions 
    specified in this AD are intended to prevent failure of an attachment 
    spring, which could cause loss of the fairing, damage to the tail 
    rotor, and subsequent loss of control of the helicopter.
    
    DATES: Effective December 14, 1998.
        Comments for inclusion in the Rules Docket must be received on or 
    before January 26, 1999.
    
    ADDRESSES: Submit comments in triplicate to the Federal Aviation 
    Administration (FAA), Office of the Regional Counsel, Southwest Region, 
    Attention: Rules Docket No. 98-SW-05-AD, 2601 Meacham Blvd., Room 663, 
    Fort Worth, Texas 76137.
    
    FOR FURTHER INFORMATION CONTACT: Mr. Shep Blackman, Aerospace Engineer, 
    FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham 
    Blvd., Fort Worth, Texas 76137, telephone (817) 222-5296, fax (817) 
    222-5961.
    
    SUPPLEMENTARY INFORMATION: The Direction Generale De L'Aviation Civile 
    (DGAC), which is the airworthiness authority for France, recently 
    notified the FAA that an unsafe condition may exist on Eurocopter 
    France Model AS-365N2, SA-360C, SA-365C, C1, C2, N, N1, and SA-366G1 
    helicopters. The DGAC advises that inspecting for broken or out-of-
    tolerance attachment springs on the fairing, replacing broken 
    attachment springs and attachment
    
    [[Page 65549]]
    
    springs that are out-of-tolerance, and marking the fairing are 
    necessary due to reports of broken attachment springs.
        Eurocopter France has issued SA-360C, SA-365C, C1, C2 Service 
    Bulletin No. 01.34, dated 96-14(N); SA-365N Service Bulletin No. 
    01.00.43, dated 96-14(N); SA-365N1, AS-365N2 Service Bulletin No. 
    01.00.42, dated 96-14(N), and SA-366G1 Service Bulletin No. 01.22, 
    dated 96-14(N). These service bulletins specify several actions 
    regarding the fairing and attachment springs. The DGAC classified these 
    service bulletins as mandatory and issued AD 95-107-039(B)R1 and AD 95-
    112-040(B), both dated June 7, 1995, and AD 95-108-018(B), dated May 
    24, 1995, in order to assure the continued airworthiness of these 
    helicopters in France.
        These helicopter models are manufactured in France and are type 
    certificated for operation in the United States under the provisions of 
    section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
    the applicable bilateral airworthiness agreement. Pursuant to this 
    bilateral airworthiness agreement, the DGAC has kept the FAA informed 
    of the situation previously described. The FAA has examined the 
    findings of the DGAC, reviewed all available information, and 
    determined that AD action is necessary for products of this type design 
    that are certificated for operation in the United States.
        Since an unsafe condition has been identified that is likely to 
    exist or develop on other Model AS-365N2, SA-360C, SA-365C, C1, C2, N, 
    N1, and SA-366G1 helicopters of the same type design registered in the 
    United States, this AD is being issued to prevent failure of the 
    attachment springs which could cause loss of the tail rotor hub 
    fairing, damage to the tail rotor, and subsequent loss of control of 
    the helicopter. This AD requires inspecting for broken or out-of-
    tolerance attachment springs on the fairing, replacing broken 
    attachment springs and those that are out-of-tolerance, and marking the 
    fairing with an ``X'' by the fairing part number to indicate 
    compliance.
        The short compliance time involved is required because the 
    previously described critical unsafe condition can adversely affect the 
    controllability of the helicopter. Therefore, the inspections, 
    replacement, and marking are required prior to further flight, and this 
    AD must be issued immediately.
        Since a situation exists that requires the immediate adoption of 
    this regulation, it is found that notice and opportunity for prior 
    public comment hereon are impracticable, and that good cause exists for 
    making this amendment effective in less than 30 days.
        The FAA estimates that 135 helicopters of U.S. registry will be 
    affected by this AD, that it will take 1.5 work hours per helicopter to 
    accomplish the actions, and that the average labor rate is $60 per work 
    hour. Required parts will cost approximately $988 per helicopter. Based 
    on these figures, the total cost impact of this AD on U.S. operators is 
    estimated to be $145,530.
    
    Comments Invited
    
        Although this action is in the form of a final rule that involves 
    requirements affecting flight safety and, thus, was not preceded by 
    notice and an opportunity for public comment, comments are invited on 
    this rule. Interested persons are invited to comment on this rule by 
    submitting such written data, views, or arguments as they may desire. 
    Communications should identify the Rules Docket number and be submitted 
    in triplicate to the address specified under the caption ADDRESSES. All 
    communications received on or before the closing date for comments will 
    be considered, and this rule may be amended in light of the comments 
    received. Factual information that supports the commenter's ideas and 
    suggestions is extremely helpful in evaluating the effectiveness of the 
    AD action and determining whether additional rulemaking action would be 
    needed.
        Comments are specifically invited on the overall regulatory, 
    economic, environmental, and energy aspects of the rule that might 
    suggest a need to modify the rule. All comments submitted will be 
    available, both before and after the closing date for comments, in the 
    Rules Docket for examination by interested persons. A report that 
    summarizes each FAA-public contact concerned with the substance of this 
    AD will be filed in the Rules Docket.
        Commenters wishing the FAA to acknowledge receipt of their comments 
    submitted in response to this rule must submit a self-addressed, 
    stamped postcard on which the following statement is made: ``Comments 
    to Docket No. 98-SW-05-AD.'' The postcard will be date stamped and 
    returned to the commenter.
        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.
        The FAA has determined that this regulation is an emergency 
    regulation that must be issued immediately to correct an unsafe 
    condition in aircraft, and that it is not a ``significant regulatory 
    action'' under Executive Order 12866. It has been determined further 
    that this action involves an emergency regulation under DOT Regulatory 
    Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
    determined that this emergency regulation otherwise would be 
    significant under DOT Regulatory Policies and Procedures, a final 
    regulatory evaluation will be prepared and placed in the Rules Docket. 
    A copy of it, if filed, 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 U.S.C. 106(g), 40113, 44701.
    
    
    Sec. 39.13  [Amended]
    
        2. Section 39.13 is amended by adding a new airworthiness directive 
    to read as follows:
    
    AD 98-24-32 Eurocopter France: Amendment 39-10918. Docket No. 98-SW-
    05-AD.
    
        Applicability: Model AS-365N2, SA-360C, SA-365C, C1, C2, N, N1, 
    and SA-366G1, 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 (e) 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
    
    [[Page 65550]]
    
    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 failure of an attachment spring (spring), which could 
    cause loss of the tail rotor hub fairing (fairing), damage to the 
    tail rotor, and subsequent loss of control of the helicopter, 
    accomplish the following:
        (a) Before further flight with fairing, part number (P/N) 
    360A33-1079-01, installed, that has modification 365A07-64B20 
    incorporated but is not marked with an ``X'' after the part number:
        (1) Remove the six fairing attachment bolts (bolts), then remove 
    the fairing from the helicopter.
        (2) Inspect for broken springs, especially in the rounded 
    sections at the rotor hub groove (Point A, Figure 1).
    
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        (3) If any broken springs are discovered, replace them with 
    airworthy springs using the procedure specified in paragraph (b) of 
    this AD.
        (4) Lubricate the threads with NATO 156 oil, then reinstall the 
    six bolts, torqued to 0.4-0.5 m.daN (35.3-44.2 in.-lbs.).
        (5) Inspect for interference between the spring and the fairing 
    (Point B, Figure 2), and replace any spring that exhibits such 
    interference in accordance with the procedure specified in paragraph 
    (b) of this AD.
        (6) Measure the outward axial protrusion (Dimension e, Figure 
    1), for each spring. If the protrusion dimension obtained from the 
    measurement required by paragraph (a)(6) of this AD is less than 1mm 
    (0.039-inches), or greater than 2.7mm (0.106 inches), either
        (i) replace the spring with an airworthy spring before further 
    flight or,
        (ii) Inspect the out-of-tolerance spring(s) in accordance with 
    paragraph (a)(2) before the first flight of each day until each 
    spring is replaced with an airworthy spring. Any out-of-tolerance 
    spring must be replaced with an airworthy spring within 25 hours 
    time-in-service (TIS).
        (b) Replace a broken or out-of-tolerance spring as follows:
        (1) Remove the spring attachment rivet.
        (2) Temporarily install an airworthy spring, P/N 360A33-1078-01, 
    and verify that the axial protrusion (Dimension e, Figure 1) is 
    within tolerance and that no interference (see Figure 2) exists.
        (3) Permanently secure the new spring to the fairing with one 
    ASN-A0078B402 rivet, coated with Mastinox 6856KD150-2, and installed 
    with the rivet head on the outside of the fairing (see Figure 1).
        (4) Mark an ``X'' after the fairing part number using indelible 
    ink after completing all inspections and spring replacements, as 
    required.
        (c) Reinstall the fairing.
        (d) If one or more springs are replaced, rebalance the tail 
    rotor head.
        (e) An alternative method of compliance or adjustment of the 
    compliance time that provides an acceptable level of safety may be 
    used if approved by the Manager, Rotorcraft Standards Staff, 
    Rotorcraft Directorate, FAA. 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 2: Information concerning the existence of approved 
    alternative methods of compliance with this AD, if any, may be 
    obtained from the Rotorcraft Standards Staff.
    
        (f) Special flight permits will not be issued.
        (g) This amendment becomes effective on December 14, 1998.
    
        Note 3: The subject of this AD is addressed in Direction 
    Generale De L'Aviation Civile (France) AD 95-107-039(B)R1 and AD 95-
    112-040(B), both dated June 7, 1995, and AD 95-108-018(B), dated May 
    24, 1995.
    
        Issued in Fort Worth, Texas, on November 19, 1998.
    Eric Bries,
    Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
    [FR Doc. 98-31589 Filed 11-25-98; 8:45 am]
    BILLING CODE 4910-13-U
    
    
    

Document Information

Effective Date:
12/14/1998
Published:
11/27/1998
Department:
Federal Aviation Administration
Entry Type:
Rule
Action:
Final rule; request for comments.
Document Number:
98-31589
Dates:
Effective December 14, 1998.
Pages:
65548-65552 (5 pages)
Docket Numbers:
Docket No. 98-SW-05-AD, Amendment 39-10918, AD 98-24-32
RINs:
2120-AA64: Airworthiness Directives
RIN Links:
https://www.federalregister.gov/regulations/2120-AA64/airworthiness-directives
PDF File:
98-31589.pdf
CFR: (1)
14 CFR 39.13