98-29375. Airworthiness Directives; Eurocopter Deutschland GmbH Model EC 135 Helicopters  

  • [Federal Register Volume 63, Number 212 (Tuesday, November 3, 1998)]
    [Rules and Regulations]
    [Pages 59206-59208]
    From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
    [FR Doc No: 98-29375]
    
    
    
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    DEPARTMENT OF TRANSPORTATION
    
    Federal Aviation Administration
    
    14 CFR Part 39
    
    [Docket No. 98-SW-35-AD; Amendment 39-10866; AD 98-15-25]
    RIN 2120-AA64
    
    
    Airworthiness Directives; Eurocopter Deutschland GmbH Model EC 
    135 Helicopters
    
    AGENCY: Federal Aviation Administration, DOT.
    
    ACTION: Final rule; request for comments.
    
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    SUMMARY: This document publishes in the Federal Register an amendment 
    adopting Airworthiness Directive (AD) 98-15-25, which was sent 
    previously to all known U.S. owners and operators of Eurocopter 
    Deutschland GmbH Model EC 135 helicopters by individual letters. This 
    AD supersedes AD 98-09-11, applicable to Eurocopter Deutschland GmbH 
    Model EC 135 helicopters, that required, before further flight, a tail 
    rotor drive shaft vibration survey and installation of a Fenestron 
    Shaft Retrofit Kit; inspecting the tail rotor drive shaft bearing 
    (bearing) attaching lock plates for bent-open tabs, and broken or 
    missing slippage marks; and visually inspecting each bearing support 
    for cracks. This AD requires the same actions as the superseded AD, 
    however it changes the required compliance time for the repetitive 
    inspections. This amendment is prompted by reports of loose bearings 
    and attachment bolts. This condition, if not corrected, could result in 
    loose bearing attachment bolts, or cracked bearing supports, which 
    could result in loss of drive to the tail rotor and subsequent loss of 
    control of the helicopter.
    
    DATES: Effective November 18, 1998, to all persons except those persons 
    to whom it was made immediately effective by priority letter AD 98-15-
    25, issued on July 17, 1998, which contained the requirements of this 
    amendment.
        Comments for inclusion in the Rules Docket must be received on or 
    before January 4, 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-35-AD, 2601 Meacham Blvd., Room 663, 
    Fort Worth, Texas 76137.
    
    FOR FURTHER INFORMATION CONTACT: Mr. Scott Horn, Aerospace Engineer, 
    FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham 
    Blvd., Fort Worth, Texas 76137, telephone (817) 222-5125, fax (817) 
    222-5961.
    
    SUPPLEMENTARY INFORMATION: On July 17, 1998, the FAA issued priority 
    letter AD 98-15-25, applicable to Eurocopter Deutschland GmbH Model EC 
    135 helicopters, which requires, before further flight, a tail rotor 
    drive shaft vibration survey and installation of a Fenestron Shaft 
    Retrofit Kit L 535M3002 882; before further flight, and thereafter at 
    intervals not to exceed 15 hours time-in-service (TIS), inspecting the 
    bearing attaching lock plates for bent-open tabs, and broken or missing 
    slippage marks; and before further flight, and thereafter at intervals 
    not to exceed 3 hours TIS, visually inspecting each bearing support for 
    cracks. That action was prompted by several reports of loose tail rotor 
    drive shaft bearings and attachment bolts. This condition, if not 
    corrected, could result in loose bearing attachment bolts, or cracked 
    bearing supports, which could result in loss of drive to the tail rotor 
    and subsequent loss of control of the helicopter.
        The FAA previously issued AD 98-09-11 on June 18, 1998 (63 FR 
    34796, June 26, 1998). AD 98-09-11 contained the same requirements as 
    this AD except that this AD requires the repetitive visual inspection 
    of each bearing support to be conducted at intervals not to exceed 3 
    hours TIS instead of the previous 15 hours TIS.
        Since the issuance of AD 98-09-11, it has been determined that 
    cracks can form in additional areas outside the bend radius of the 
    bearing support, and that the cracks can form and propagate to failure 
    within the previously-required 15 hours TIS inspection interval.
        The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority 
    for the Federal Republic of Germany, recently notified the FAA that an 
    unsafe condition may exist on Eurocopter Deutschland GmbH Model EC 135 
    helicopters. The LBA advises that loosening of bolt connections at 
    bearing supports may lead to a tail rotor failure and loss of the 
    helicopter. The LBA issued AD 1998-033/6, dated July 9, 1998, 
    applicable to ECD Model EC 135 helicopters.
        The FAA has reviewed Eurocopter EC 135 Alert Service Bulletin No. 
    EC 135-53A-002, Revision 1, dated July 7, 1998, which describes 
    procedures for visually inspecting the bearing supports, and Eurocopter 
    EC 135 Alert Service Bulletin No. EC 135-53A-005, Revision 1, dated 
    April 6, 1998, which describes procedures for measuring vibrations on 
    the tail rotor drive shaft and replacing roller bearing attaching 
    hardware at bearing locations.
        This helicopter model is manufactured in the Federal Republic of 
    Germany and is type certificated for operation in the United States 
    under the provision 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 LBA 
    has kept the FAA informed of the situation described above. The FAA has 
    examined the findings of the LBA, reviewed all available information, 
    and determined that AD action is necessary for products of this type 
    design that are certificated for operations in the United States.
        Since an unsafe condition has been identified that is likely to 
    exist or develop on other Eurocopter Deutschland GmbH Model EC 135 
    helicopters of the same type design, this AD requires, before further 
    flight, a tail rotor drive shaft vibration survey and installation of a 
    Fenestron Shaft Retrofit Kit L 535M3002 882. Also, before further 
    flight, and thereafter at intervals not to exceed 15 hours TIS, the AD 
    requires inspecting the bearing attaching lock plates at each bearing 
    support for bent-open tabs, and inspecting for broken or missing 
    slippage marks. If a bearing attaching lock plate tab is bent open, or 
    if a slippage mark is broken or missing, the FAA must be notified. 
    Finally, the AD requires, before further flight, and thereafter at 
    intervals not to exceed 3 hours TIS, inspecting the bearing supports 
    for cracks in the areas shown in the attached Figure 1, from the bend 
    radius to the attaching screws and rivets connecting the bearing 
    supports to the tailboom. Use of a 6-power or higher magnifying glass 
    and a bright light are required for this inspection. If a crack is 
    found, the cracked bearing support is to be replaced with an airworthy 
    bearing support.
        The short compliance time involved is required because the 
    previously described critical unsafe condition can adversely affect the 
    structural integrity and controllability of the aircraft. Therefore, 
    the installation and an inspection are required before further flight, 
    and this AD must be issued immediately.
        Since it was found that immediate corrective action was required, 
    notice and opportunity for prior public comment thereon were 
    impracticable and contrary to the public interest, and good cause 
    existed to make the AD effective immediately by individual letters 
    issued on July 17, 1998 to all known U.S. owners and operators of 
    Eurocopter Deutschland GmbH Model EC 135 helicopters. These conditions 
    still exist, and the AD is hereby
    
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    published in the Federal Register as an amendment to section 39.13 of 
    the Federal Aviation Regulations (14 CFR 39.13) to make it effective to 
    all persons. The only difference between the priority letter AD and 
    this published version of this AD is that a NOTE 2 is added to this AD 
    to inform the reader that the procedures and limits for the vibration 
    survey are contained in Eurocopter Deutschland document D/TA 13/98, 
    Revision 01. This note is informational only and is not a substantive 
    change.
        The FAA estimates that 6 helicopters of U.S. registry will be 
    affected by this AD. The 15 hours TIS inspection will take 
    approximately 0.5 work hours and the 3 hours TIS inspection will take 
    approximately 1.5 work hours. The average labor rate is $60 per work 
    hour. The manufacturer has represented that they will accomplish this 
    vibration survey and the installation of the Fenestron Shaft Retrofit 
    kit at no cost to the owners/operators. Assuming the helicopters are 
    operated 900 hours TIS per year, the total cost impact of the AD on 
    U.S. operators for one year is estimated to be $172,800.
    
    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-35-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 removing Amendment 39-10632 (63 FR 
    34796, June 26, 1998) and by adding a new airworthiness directive to 
    read as follows:
    
    98-15-25  Eurocopter Deutschland: Amendment 39-10866. Docket No. 98-
    SW-35-AD. Supersedes AD 98-09-11, Amendment 39-10632, Docket No. 98-
    SW-18-AD.
    
        Applicability: Model EC 135 helicopters, 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 detect loose tail rotor drive shaft bearing (bearing) 
    attachment bolts, or cracked bearing supports, which could result in 
    loss of drive to the tail rotor and subsequent loss of control of 
    the helicopter, accomplish the following:
        (a) Before further flight, conduct a tail rotor drive shaft 
    vibration survey and install a Fenestron Shaft Retrofit Kit L 
    535M3002 882.
    
        Note 2: Procedures and limits for the vibration survey are 
    provided in Eurocopter Deutschland document D/TA 13/98 Revision 01.
    
        (b) Before further flight, and thereafter at intervals not to 
    exceed 15 hours time-in-service (TIS), at each bearing support:
        (1) Inspect each bearing attaching lock plate that was installed 
    with the Fenestron Shaft Retrofit Kit L 535M3002 882 for bent-open 
    tabs.
        (2) Inspect for broken or missing slippage marks that may 
    indicate looseness or rotation of attaching hardware.
        (3) If a lock plate tab is bent open on bearing supports A, B, 
    or C (shown in Figure 1), or if slippage marks are broken or 
    missing, contact the Manager, Rotorcraft Standards Staff, FAA, 
    telephone (817) 222-5110, fax (817) 222-5961.
    
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    [GRAPHIC] [TIFF OMITTED] TR03NO98.028
    
    
    
        (c) Before further flight, and thereafter at intervals not to 
    exceed 3 hours TIS, using a 6-power or higher magnifying glass and a 
    bright light, visually inspect bearing supports B and C as shown in 
    Figure 1, from the bend radius to the attaching screws and rivets 
    connecting the bearing supports to the tailboom. If a crack is 
    found, replace the bearing support with an airworthy bearing 
    support.
        (d) 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, 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 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 will not be issued.
        (f) This amendment becomes effective on November 18, 1998, to 
    all persons except those persons to whom it was made immediately 
    effective by Priority Letter AD 98-15-25, issued July 17, 1998, 
    which contained the requirements of this amendment.
    
        Note 4: The subject of this AD is addressed in Luftfahrt-
    Bundesamt (Federal Republic of Germany) AD 1998-033/6, dated July 9, 
    1988.
    
        Issued in Fort Worth, Texas, on October 27, 1998.
    Eric Bries,
    Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
    [FR Doc. 98-29375 Filed 11-2-98; 8:45 am]
    BILLING CODE 4910-13-P
    
    
    

Document Information

Effective Date:
11/18/1998
Published:
11/03/1998
Department:
Federal Aviation Administration
Entry Type:
Rule
Action:
Final rule; request for comments.
Document Number:
98-29375
Dates:
Effective November 18, 1998, to all persons except those persons to whom it was made immediately effective by priority letter AD 98-15- 25, issued on July 17, 1998, which contained the requirements of this amendment.
Pages:
59206-59208 (3 pages)
Docket Numbers:
Docket No. 98-SW-35-AD, Amendment 39-10866, AD 98-15-25
RINs:
2120-AA64: Airworthiness Directives
RIN Links:
https://www.federalregister.gov/regulations/2120-AA64/airworthiness-directives
PDF File:
98-29375.Pdf
CFR: (1)
14 CFR 39.13