98-30048. Airworthiness Directives; Burkhart GROB Luft-und Raumfahrt GmbH Model G 109B Gliders  

  • [Federal Register Volume 63, Number 218 (Thursday, November 12, 1998)]
    [Rules and Regulations]
    [Pages 63137-63139]
    From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
    [FR Doc No: 98-30048]
    
    
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    DEPARTMENT OF TRANSPORTATION
    
    Federal Aviation Administration
    
    14 CFR Part 39
    
    [Docket No. 98-CE-72-AD; Amendment 39-10876; AD 98-23-10]
    RIN 2120-AA64
    
    
    Airworthiness Directives; Burkhart GROB Luft-und Raumfahrt GmbH 
    Model G 109B Gliders
    
    AGENCY: Federal Aviation Administration, DOT.
    
    ACTION: Final rule.
    
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    SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
    applies to all Burkhart GROB Luft-und Raumfahrt GmbH (Grob) Model G 
    109B gliders. This AD requires inspecting the engine mounting frame for 
    paint scratches and damage (abrasions, notches, or chafing); and 
    repairing any paint scratches, and repairing or replacing any engine 
    mounting frame that is found damaged. This AD is the result of 
    mandatory continuing airworthiness information (MCAI) issued by the 
    airworthiness authority for Germany. The actions specified by this AD 
    are intended to detect and correct damage to the engine mounting frame, 
    which could result in failure of the engine mount structure with 
    consequent loss of the engine.
    
    DATES: Effective December 17, 1998.
        The incorporation by reference of certain publications listed in 
    the regulations is approved by the Director of the Federal Register as 
    of December 17, 1998.
    
    ADDRESSES: Service information that applies to this AD may be obtained 
    from Grob-Werke GmbH & Co. KG, Unternehmensbereich, Burkhart Grob 
    Flugzeugbau, Flugplatz Mattsies, 86874 Tussenhausen, Germany. This 
    information may also be examined at the Federal Aviation Administration 
    (FAA), Central Region, Office of the Regional Counsel, Attention: Rules 
    Docket No. 98-CE-72-AD, Room 1558, 601 E. 12th Street, Kansas City, 
    Missouri 64106; or at the Office of the Federal Register, 800 North 
    Capitol Street, NW, suite 700, Washington, DC.
    
    FOR FURTHER INFORMATION CONTACT: Mr. Mike Kiesov, Aerospace Engineer, 
    FAA, Small Airplane Directorate, 1201 Walnut, suite 900, Kansas City, 
    Missouri 64106; telephone: (816) 426-6932; facsimile: (816) 426-2169.
    
    SUPPLEMENTARY INFORMATION:
    
    Events Leading to the Issuance of This AD
    
        A proposal to amend part 39 of the Federal Aviation Regulations (14 
    CFR part 39) to include an AD that would apply to all Grob Model G 109B 
    gliders was published in the Federal Register as a notice of proposed 
    rulemaking (NPRM) on September 2, 1998 (63 FR 46714). The NPRM proposed 
    to require inspecting the engine mounting frame for paint scratches and 
    damage (abrasions, notches, or chafing); and repairing any paint 
    scratches, and repairing or replacing any engine mounting frame that is 
    found damaged. Accomplishment of the proposed action as specified in 
    the NPRM would be in accordance with Grob Service Bulletin TM 817-45, 
    dated July 27, 1995.
        The NPRM was the result of mandatory continuing airworthiness 
    information (MCAI) issued by the airworthiness authority for Germany.
        Interested persons have been afforded an opportunity to participate 
    in the making of this amendment. No comments were received on the 
    proposed rule or the FAA's determination of the cost to the public.
    
    The FAA's Determination
    
        After careful review of all available information related to the 
    subject presented above, the FAA has determined that air safety and the 
    public interest require the adoption of the rule as proposed except for 
    minor editorial corrections. The FAA has determined that these minor 
    corrections will not change the meaning of the AD and will not add any 
    additional burden upon the public than was already proposed.
    
    Cost Impact
    
        The FAA estimates that 29 gliders in the U.S. registry will be 
    affected by the
    
    [[Page 63138]]
    
    inspection, that it will take approximately 2 workhours per glider to 
    accomplish the inspection, and that the average labor rate is 
    approximately $60 an hour. Based on these figures, the total cost 
    impact of the inspection on U.S. operators is estimated to be $3,480, 
    or $120 per glider.
        If damage is found on the engine mounting frame that is beyond 
    certain limits specified in the service information, the FAA estimates 
    that it will take approximately 13 workhours per glider to accomplish 
    the repair or replacement, at an average labor rate of approximately 
    $60 an hour. Parts cost $200 for repair and $750 for replacement. Based 
    on these figures, the total cost impact of the repair, if necessary, is 
    estimated to be $980 per glider. The total cost impact of the 
    replacement, if necessary, is estimated to be $1,530 per glider.
    
    Compliance Time of This AD
    
        Although damage to the engine mounting frame occurs during flight, 
    this unsafe condition is not a result of the number of times the glider 
    is operated. The chance of this situation occurring is the same for a 
    glider with 10 hours time-in-service (TIS) as it will be for a glider 
    with 500 hours TIS. For this reason, the FAA has determined that a 
    compliance based on calendar time should be utilized in this AD in 
    order to assure that the unsafe condition is addressed on all gliders 
    in a reasonable time period.
    
    Regulatory Impact
    
        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 copy of the final evaluation prepared for this 
    action is contained in the Rules Docket. A copy of it may be obtained 
    by contacting the Rules Docket at the location provided under the 
    caption ADDRESSES.
    
    List of Subjects in 14 CFR Part 39
    
        Air transportation, Aircraft, Aviation safety, Incorporation by 
    reference, 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 
    (AD) to read as follows:
    
    98-23-10  Burkhart Grob Luft-und Raumfahrt GmbH: Amendment 39-10876; 
    Docket No. 98-CE-72-AD.
        Applicability: Model G 109B gliders, all serial numbers, 
    certificated in any category.
    
        Note 1: This AD applies to each glider 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 gliders that have been modified, 
    altered, or repaired so that the performance of the requirements of 
    this AD is affected, the owner/operator must request approval for an 
    alternative method of compliance in accordance with paragraph (g) of 
    this AD. The request should include an assessment of the effect of 
    the modification, alteration, or repair on the unsafe condition 
    addressed by this AD; and, if the unsafe condition has not been 
    eliminated, the request should include specific proposed actions to 
    address it.
    
        Compliance: Required as indicated in the body of this AD, unless 
    already accomplished.
        To detect and correct damage to the engine mounting frame, which 
    could result in failure of the engine mount structure with 
    consequent loss of the engine, accomplish the following:
        (a) Within the next 3 calendar months after the effective date 
    of this AD, inspect the engine mounting frame for paint scratches 
    and damage (abrasions, notches, or chafing) in accordance with the 
    Action section of Grob Service Bulletin TM 817-45, dated July 27, 
    1995.
        (b) If a paint scratch(es), but no damage, is found during the 
    inspection required by paragraph (a) of this AD, prior to further 
    flight, remove all flakes and dust from the area, degrease the tube 
    and apply a protective anti-corrosion coat, and shorten the warm air 
    duct or replace it if damaged. Accomplish the warm air duct 
    modification or replacement in accordance with the maintenance 
    manual.
        (c) If a paint scratch(es) and damage are both found during the 
    inspection required by paragraph (a) of this AD, accomplish the 
    following:
        (1) Prior to further flight, remove all flakes and dust from the 
    area; and
        (2) Perform the actions specified in paragraph (d) or (e) of 
    this AD, as applicable. Accomplish these actions at the compliance 
    times specified in the applicable paragraphs.
        (d) If damage (abrasions, notches, or chafing) is found during 
    the inspection required by paragraph (a) of this AD, and the damage 
    is 0.7 millimeters (mm) or less in depth as specified in paragraph 
    3(b) of the Action section of Grob Service Bulletin TM 817-45, dated 
    July 27, 1995, prior to further flight, degrease the tube and apply 
    a protective anti-corrosion coat, and shorten the warm air duct or 
    replace it if damaged. Accomplish the warm air duct modification or 
    replacement in accordance with the maintenance manual. Within 6 
    calendar months after the inspection required by paragraph (a) of 
    this AD, accomplish one of the following:
        (1) Send the engine mounting frame to the manufacturer for 
    repair at the address specified in paragraph (h) of this AD and 
    accomplish the warm air duct modification or replacement specified 
    in paragraph (b) of this AD. Do not operate the glider until the 
    part is repaired, sent back, and re-installed on the glider; or
        (2) Replace the engine mounting frame with a new part of the 
    same design, or an FAA-approved part that has been inspected in 
    accordance with the requirements of paragraph (a) of this AD and is 
    found free of damage.
        (e) If damage (abrasions, notches, or chafing) is found during 
    the inspection required by paragraph (a) of this AD, and the damage 
    is more than 0.7 mm in depth as specified in paragraph 3(c) of the 
    Action section of Grob Service Bulletin TM 817-45, dated July 27, 
    1995, prior to further flight, accomplish one of the following:
        (1) Send the engine mounting frame to the manufacturer for 
    repair at the address specified in paragraph (h) of this AD and 
    accomplish the warm air duct modification or replacement specified 
    in paragraph (b) of this AD. Do not operate the glider until the 
    part is repaired, sent back, and re-installed on the glider; or
        (2) Replace the engine mounting frame with a new part of the 
    same design, or an FAA-approved part that has been inspected in 
    accordance with the requirements of paragraph (a) of this AD and is 
    found free of damage. Accomplish the warm air duct modification or 
    replacement specified in paragraph (b) of this AD.
        (f) 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 glider to a location where the 
    requirements of this AD can be accomplished.
        (g) An alternative method of compliance or adjustment of the 
    compliance times that provides an equivalent level of safety may be 
    approved by the Manager, Small Airplane Directorate, 1201 Walnut, 
    suite 900, Kansas City, Missouri 64106. The request shall be
    
    [[Page 63139]]
    
    forwarded through an appropriate FAA Maintenance Inspector, who may 
    add comments and then send it to the Manager, Small Airplane 
    Directorate.
    
        Note 2: Information concerning the existence of approved 
    alternative methods of compliance with this AD, if any, may be 
    obtained from the Small Airplane Directorate.
    
        (h) Questions or technical information related to Grob Service 
    Bulletin TM 817-45, dated July 27, 1995, should be directed to Grob-
    Werke GmbH & Co. KG, Unternehmensbereich, Burkhart Grob Flugzeugbau, 
    Flugplatz Mattsies, 86874 Tussenhausen, Germany. This service 
    information may be examined at the FAA, Central Region, Office of 
    the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, 
    Missouri 64106.
        (i) The inspection required by this AD shall be done in 
    accordance with Grob Service Bulletin TM 817-45, dated July 27, 
    1995. This incorporation by reference was approved by the Director 
    of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR 
    part 51. Copies may be obtained from Grob-Werke GmbH & Co. KG, 
    Unternehmensbereich, Burkhart Grob Flugzeugbau, Flugplatz Mattsies, 
    86874 Tussenhausen, Germany. Copies may be inspected at the FAA, 
    Central Region, Office of the Regional Counsel, Room 1558, 601 E. 
    12th Street, Kansas City, Missouri, or at the Office of the Federal 
    Register, 800 North Capitol Street, NW, suite 700, Washington, DC.
    
        Note 3: The subject of this AD is addressed in German AD 95-362 
    Grob, dated September 27, 1995.
    
        (j) This amendment becomes effective on December 17, 1998.
    
        Issued in Kansas City, Missouri, on November 2, 1998.
    Michael Gallagher,
    Manager, Small Airplane Directorate, Aircraft Certification Service.
    [FR Doc. 98-30048 Filed 11-10-98; 8:45 am]
    BILLING CODE 4910-13-U
    
    
    

Document Information

Effective Date:
12/17/1998
Published:
11/12/1998
Department:
Federal Aviation Administration
Entry Type:
Rule
Action:
Final rule.
Document Number:
98-30048
Dates:
Effective December 17, 1998.
Pages:
63137-63139 (3 pages)
Docket Numbers:
Docket No. 98-CE-72-AD, Amendment 39-10876, AD 98-23-10
RINs:
2120-AA64: Airworthiness Directives
RIN Links:
https://www.federalregister.gov/regulations/2120-AA64/airworthiness-directives
PDF File:
98-30048.pdf
CFR: (1)
14 CFR 39.13