96-22575. Airworthiness Directives; Bell Helicopter Textron, A Division of Textron Canada Ltd. Model 222, 222B, 222U, and 230 Helicopters  

  • [Federal Register Volume 61, Number 174 (Friday, September 6, 1996)]
    [Rules and Regulations]
    [Pages 47041-47046]
    From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
    [FR Doc No: 96-22575]
    
    
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    DEPARTMENT OF TRANSPORTATION
    
    Federal Aviation Administration
    
    14 CFR Part 39
    
    [Docket No. 96-SW-08-AD; Amendment 39-9740; AD 96-18-15]
    RIN 2120-AA64
    
    
    Airworthiness Directives; Bell Helicopter Textron, A Division of 
    Textron Canada Ltd. Model 222, 222B, 222U, and 230 Helicopters
    
    AGENCY: Federal Aviation Administration, DOT.
    
    ACTION: Final rule; request for comments.
    
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    SUMMARY: This amendment supersedes an existing airworthiness directive 
    (AD) 96-01-08, which superseded Priority Letter AD 95-23-02, both of 
    which were applicable to certain serial-numbered Bell Helicopter 
    Textron, A Division of Textron Canada Ltd. (BHT) Model 222, 222B, 222U, 
    and 230 helicopters, that currently requires an initial check of both 
    surfaces of each tail rotor blade (blade) for cracks; an inspection of 
    the blade skin if a crack of a specified size or location is found in 
    the paint; and replacement of the blade if a crack is found in the 
    blade skin. This AD requires the same actions as required by the 
    existing AD, but expands the applicability to include additional blade 
    part numbers (P/N). This amendment is prompted by three incidents in 
    which a crack developed in the stainless steel blade skins due to 
    sanding marks on the blades that occurred during the manufacturing 
    process on BHT Model 230 helicopters, which are similar in design to 
    the Model 222, 222B and 222U helicopters. The actions specified by this 
    AD are intended to prevent failure of a blade due to a fatigue crack, 
    loss of the tail rotor and tail rotor gear box, and subsequent loss of 
    control of the helicopter.
    
    DATES: Effective September 23, 1996.
        Comments for inclusion in the Rules Docket must be received on or 
    before November 5, 1996.
    
    ADDRESSES: Submit comments in triplicate to the Federal Aviation 
    Administration (FAA), Office of the Assistant Chief Counsel, Attention: 
    Rules Docket No. 96-SW-08-AD, 2601 Meacham Blvd., Room 663, Fort Worth, 
    Texas 76137.
    
    FOR FURTHER INFORMATION CONTACT: Mr. Charles Harrison, Aerospace 
    Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 
    Fort Worth, Texas 76193-0170, telephone (817) 222-5447, fax (817) 222-
    5960.
    
    SUPPLEMENTARY INFORMATION: On November 3, 1995, the FAA issued priority 
    letter AD 95-23-02, applicable to certain serial-numbered BHT Model 
    222, 222B, 222U, and 230 helicopters, to require an initial check of 
    both surfaces of each blade for cracks; an inspection of the blade skin 
    if a crack of a specified size or location was found in the paint; and 
    replacement of the blade if a crack was found in the blade skin. That 
    action was prompted by two incidents in which a crack developed in the 
    stainless steel blade skins on BHT Model 230 helicopters. In one of 
    these incidents, the blade failed during flight. Subsequent 
    investigation revealed fatigue cracks originating from sanding marks on 
    the blade skin. The cracks were located just outboard of the stainless 
    steel blade doubler. That condition, if not corrected, could result in 
    failure of a blade due to a fatigue crack, loss of the tail rotor and 
    tail rotor gear box, and subsequent loss of control of the helicopter. 
    Subsequent to the issuance of the priority letter AD, the FAA issued AD 
    96-01-08 to publish the
    
    [[Page 47042]]
    
    priority letter in the Federal Register and to correct an error in the 
    applicability paragraph of the priority letter AD, which incorrectly 
    stated the serial number (S/N) of one of the affected models. The Model 
    230 helicopters affected by the AD include S/N 23001 through 23038. The 
    priority letter AD incorrectly stated S/N 23001 through 23034.
        Since the issuance of AD 96-01-08, a crack has been discovered in 
    the tail rotor blade of another serial-numbered Model 230 helicopter, 
    that originated from a small indentation that occurred during the 
    manufacturing process. As a result of this discovery, additional part-
    numbered blades have been determined to be affected.
        Since the unsafe condition described is likely to exist or develop 
    on other BHT Model 222, 222B, 222U, and 230 helicopters of the same 
    type design, this AD supersedes AD 96-01-08 to require, before further 
    flight, an initial visual check of both painted surfaces of each blade 
    for cracks. If a crack of a specified size and location is found in the 
    paint, removal of the paint and a visual inspection using a 10-power or 
    higher magnifying glass is required before further flight. If this 
    closer inspection reveals a crack in the blade skin, replacement of the 
    blade with an airworthy blade is required. If no crack is found in the 
    blade skin, the area from which the paint was removed is coated with a 
    light-weight oil or an equivalent corrosion preventive compound, and 
    then repetitive visual checks are required at intervals not to exceed 3 
    hours time-in-service (TIS). The initial visual check that is required 
    before further flight and the repetitive checks may be performed by a 
    pilot, but must be entered into the aircraft records showing compliance 
    with paragraph (a) of this AD in accordance with sections 43.11 and 
    91.417 (a)(2)(v) of the Federal Aviation Regulations (14 CFR sections 
    43.11 and 91.417 (a)(2)(v)). This AD allows a pilot to perform this 
    check because it involves only a visual check for cracking in the 
    painted surface of the blade skin, and can be performed equally well by 
    a pilot or a mechanic.
        Since a situation exists that requires the immediate adoption of 
    this regulation, it is found that notice and opportunity for public 
    comment hereon are impracticable, and that good cause exists for making 
    this amendment effective in less than 30 days.
    
    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. 96-SW08-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 USC 106(g), 40113, 44701.
    
    
    Sec. 39.13  [Amended]
    
        2. Section 39.13 is amended by adding the following new 
    airworthiness directive (AD), Amendment 39-9740, to read as follows:
    
    AD 96-18-15 Bell Helicopter Textron, a Division of Textron Canada 
    Ltd.: Amendment 39-9740. Docket No. 96-SW08-AD. Supersedes AD 96-01-
    08, issued December 21, 1995, Docket No. 95-SW-33-AD.
        Applicability: Model 222 helicopters, serial numbers (S/N) 47006 
    through 47089, and Model 222B helicopters, S/N 47131 through 47156, 
    with tail rotor blades, part numbers (P/N) 222-016-001-101, -107, -
    111, -113, -115, and -119; Model 222U helicopters, S/N 47501 through 
    47574, with tail rotor blades, P/N 222-016-001-107, -111, and -115; 
    and Model 230 helicopters, S/N 23001 through 23038, with tail rotor 
    blades, P/N 222-016-001-111 and -115, 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 (g) 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 before further flight, unless accomplished 
    previously. To prevent failure of a tail rotor blade (blade) due to 
    a fatigue crack (see Figure 1), loss of the tail rotor and tail 
    rotor gear box, and subsequent
    
    [[Page 47043]]
    
    loss of control of the helicopter, accomplish the following:
        (a) Clean the painted surfaces of the blades in an area 
    approximately 6 inches spanwise on either side of the doubler tip. 
    Visually check both surfaces of each blade for cracks by pushing the 
    blade tip away from the surface being checked until it contacts the 
    flapping stop and then holding the blade firmly against the stop. 
    Pay particular attention to the area reaching from the doubler tip 
    to 1 inch outboard, centering on an area 2 inches aft of the blade 
    leading edge (see Figure 2).
        (b) The visual check required by paragraph (a) may be performed 
    by an owner/operator (pilot) holding at least a private pilot 
    certificate, and must be entered into the aircraft records showing 
    compliance with paragraph (a) of this AD in accordance with sections 
    43.11 and 91.417(a)(2)(v) of the Federal Aviation Regulations (14 
    CFR sections 43.11 and 91.417(a)(2)(v)).
        (c) If the visual check described in paragraph (a) reveals any 
    crack outboard of the doubler tip (Station 14.250), or any chordwise 
    crack inboard of the doubler tip that is longer than 1 inch (see 
    Figure 3), accomplish the following:
        (1) Remove the paint from the skin in the cracked area using the 
    following procedures (see Figure 4):
    
        Note 2: Paint cracking that follows the contour of the doubler 
    is common and requires no action.
    
        (2) Using a 180 or 220 grit abrasion paper, sand by hand with 
    spanwise strokes until greenish- or yellow-colored primer or bare 
    metal begins to be exposed.
        (3) Using spanwise or circular sanding motions, continue hand-
    sanding the remaining greenish- or yellow-colored primer in the 
    cracked area using a 320 or 400 grit paper until sufficient metal 
    has been exposed to allow inspection (see area indicated in Figure 
    4).
        (d) Inspect the blade skin for cracks in the area that was 
    exposed in accordance with paragraph (c) using a 10-power or higher 
    magnifying glass.
        (1) If no crack is found in the blade skin, coat the bare metal 
    area with a light-weight oil or an equivalent corrosion preventive 
    compound.
        (2) If any crack is discovered, remove the blade and replace it 
    with an airworthy blade.
        (e) Perform the requirements of this AD upon installation of a 
    replacement blade.
        (f) Perform the visual checks of paragraph (a) of this AD and 
    the subsequent inspections, if appropriate, at intervals not to 
    exceed 3 hours TIS.
    
        Note 3: A light-weight oil or equivalent corrosion preventive 
    compound may be applied after accomplishing the repetitive 
    requirements of paragraph (f) of this AD.
    
    BILLING CODE 4910-13-U
    
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    BILLING CODE 4910-13-C
    
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        (g) 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 Certification Office, 
    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 Certification 
    Office.
    
        Note 4: Information concerning the existence of approved 
    alternative methods of compliance with this AD, if any, may be 
    obtained from the Rotorcraft Certification Office.
    
        (h) Special flight permits to accomplish the requirements of 
    this AD will not be issued.
        (i) This amendment becomes effective on September 23, 1996.
    
        Issued in Fort Worth, Texas, on August 26, 1996.
    Daniel P. Salvano,
    Manager, Rotorcraft Directorate, Aircraft Certification Service.
    [FR Doc. 96-22575 Filed 9-5-96; 8:45 am]
    BILLING CODE 4910-13-U
    
    
    

Document Information

Effective Date:
9/23/1996
Published:
09/06/1996
Department:
Federal Aviation Administration
Entry Type:
Rule
Action:
Final rule; request for comments.
Document Number:
96-22575
Dates:
Effective September 23, 1996.
Pages:
47041-47046 (6 pages)
Docket Numbers:
Docket No. 96-SW-08-AD, Amendment 39-9740, AD 96-18-15
RINs:
2120-AA64: Airworthiness Directives
RIN Links:
https://www.federalregister.gov/regulations/2120-AA64/airworthiness-directives
PDF File:
96-22575.pdf
CFR: (1)
14 CFR 39.13