96-33231. Airworthiness Directives; The New Piper Aircraft, Inc. PA24, PA28R, PA30, PA32R, PA34, and PA39 Series Airplanes  

  • [Federal Register Volume 62, Number 1 (Thursday, January 2, 1997)]
    [Rules and Regulations]
    [Pages 10-15]
    From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
    [FR Doc No: 96-33231]
    
    
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    DEPARTMENT OF TRANSPORTATION
    
    Federal Aviation Administration
    
    14 CFR Part 39
    
    [Docket No. 96-CE-09-AD; Amendment 39-9872; AD 97-01-01]
    RIN 2120-AA64
    
    
    Airworthiness Directives; The New Piper Aircraft, Inc. PA24, 
    PA28R, PA30, PA32R, PA34, and PA39 Series Airplanes
    
    AGENCY: Federal Aviation Administration, DOT.
    
    ACTION: Final rule.
    
    -----------------------------------------------------------------------
    
    SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
    supersedes AD 95-20-07, which currently requires repetitively 
    inspecting the main gear sidebrace studs for cracks on certain The New 
    Piper Aircraft, Inc. (Piper) PA24, PA28R, PA30, PA32R, PA34, and PA39 
    series airplanes, and replacing any cracked main gear sidebrace stud. 
    This AD retains the repetitive inspection and possible replacement 
    requirements of AD 95-20-07; specifies in the ``Applicability'' section 
    of the AD that certain Model PA34-200T airplanes could contain a 
    certain main gear sidebrace assembly configuration that is not 
    affected; and incorporates additional modification and replacement 
    options. This AD results from additional information received by the 
    Federal Aviation Administration (FAA) after the issuance of AD 95-20-07 
    on the design and service history of the affected airplanes concerning 
    this subject. The actions specified by this AD are intended to prevent 
    a main landing gear collapse caused by main gear sidebrace stud cracks, 
    which could result in loss of control of the airplane during landing 
    operations.
    
    EFFECTIVE DATE: February 7, 1997.
    
    ADDRESSES: Information that applies to this AD may be examined at the 
    FAA, Central Region, Office of the Assistant Chief Counsel, Attention: 
    Rules Docket 96-CE-09-AD, Room 1558, 601 E. 12th Street, Kansas City, 
    Missouri 64106.
    
    FOR FURTHER INFORMATION CONTACT: Christina Marsh, Aerospace Engineer, 
    FAA, Atlanta Aircraft Certification Office, Campus Building, 1701 
    Columbia Avenue, suite 2-160, College Park, Georgia 30337-2748; 
    telephone (404) 305-7362; facsimile (404) 305-7348.
    
    SUPPLEMENTARY INFORMATION:
    
    Events Leading to This Action
    
        A proposal to amend part 39 of the Federal Aviation Regulations (14 
    CFR part 39) to include an AD that would apply to Piper PA24, PA28R, 
    PA30, PA32R, PA34, and PA39 series airplanes was published in the 
    Federal Register on April 25, 1996 (61 FR 18299). The action proposed 
    to supersede AD 95-20-07 with a new AD that would (1) retain the 
    requirement of repetitively inspecting the main gear sidebrace 
    assembly, and replacing any cracked main gear sidebrace stud. This 
    includes the inspection-terminating replacement contained in AD 95-20-
    07; (2) specify in the ``Applicability'' section of the current AD that 
    certain Piper Model PA34-200T airplanes could incorporate a main gear 
    sidebrace assembly containing the \5/8\-inch stud, part number (P/N) 
    78717-02, with a two-piece bushing, P/N 67026-09, and would not be 
    affected by the proposed AD; and (3) incorporate, as an option, an 
    inspection-terminating modification for Piper PA28R, PA32R, and PA34 
    series airplanes. This modification consists of reaming the existing 
    two-piece bushings, P/N 67026-6, to an inside diameter of .624-inch to 
    .625-inch, rechamfering the bushing, and installing the \5/8\-inch 
    stud, P/N 78717-02.
        Interested persons have been afforded an opportunity to participate 
    in the making of this amendment. Due consideration has been given to 
    the two comments received from one commenter.
    
    Comment Issue No. 1: Include a Specific FAA-Approved Parts Manufacture 
    Approval (PMA) in the AD as Replacement Parts
    
        The commenter, Webco Aircraft (Webco), states that it holds a PMA 
    for main gear sidebrace studs to equip the Piper Models PA24, PA24-250, 
    PA24-260, PA24-400, PA30, and PA39 airplanes. Webco requests that the 
    FAA
    
    [[Page 11]]
    
    reference these main gear sidebrace studs in the AD.
        The FAA does not concur. FAA policy is to not reference PMA parts 
    in AD's, unless the FAA determines that the unsafe condition applies to 
    the PMA parts. If these Webco parts are installed, then the actions of 
    this AD would not apply because the parts are an FAA-approved 
    equivalent to the Piper main gear sidebrace studs that, when installed, 
    eliminate the repetitive inspection requirement of the AD.
    
    Comment Issue No. 2: Additional Information Added to the AD
    
        Webco recommends that the FAA add cautionary information to the AD 
    on reaming and chamfering the existing two-piece bushings, P/N 67026-6, 
    on the Piper PA-28R, PA-32R, and PA-34 series airplanes. Webco states 
    that the manufacturing and service limits for the P/N 67026-6 bushings 
    are so close that reaming could induce gouges that are deeper than the 
    minimum dimension specified by The New Piper Aircraft, Inc. Webco also 
    recommends that the FAA incorporate specific guidance into the AD, 
    emphasizing that only the head side of the bushing requires chamfering 
    to accommodate the radius in the shank of the sidebrace stud.
        The FAA concurs that additional guidance on chamfering the bushing 
    would be helpful and has reworded the AD to incorporate the commenter's 
    specific recommendation.
        The FAA does not concur that more guidance is needed on reaming the 
    bushings. The proposal specifies reaming the inside diameter of the 
    bushings to a dimension of .624-inch to .625-inch. If the bushing is 
    reamed to a dimension other than that specified in the AD, then 
    compliance with the AD would not be accomplished.
    
    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 
    the incorporation of guidance on chamfering the bushings and minor 
    editorial corrections. The FAA has determined that the incorporation 
    and 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 13,200 airplanes in the U.S. registry will 
    be affected by this AD, that it will take approximately 5 workhours per 
    airplane to accomplish the required action, and that the average labor 
    rate is approximately $60 an hour. Based on these figures, the total 
    cost impact of the required inspection on U.S. operators is estimated 
    to be $3,960,000. This figure represents the total cost of the required 
    initial inspection, and does not reflect costs for any of the required 
    repetitive inspections or possible replacements. The FAA has no way of 
    determining how many main gear sidebrace studs may need replacement or 
    how many repetitive inspections each owner/operator may incur over the 
    life of the airplane.
        In addition, this AD requires the same inspections required by AD 
    95-20-07. The only difference between this AD and AD 95-20-07 is the 
    addition of an inspection-terminating modification option. This AD does 
    not provide any additional cost impacts over that already required by 
    AD 95-20-07.
    
    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, 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 removing Airworthiness Directive 
    (AD) 95-20-07, Amendment 39-9386, and by adding a new AD to read as 
    follows:
    
    97-01-01  The New Piper Aircraft, Inc.: Amendment 39-9782; Docket 
    No. 96-CE-09-AD. Supersedes AD 95-20-07, Amendment 39-9386.
    
        Applicability: The following airplane models and serial numbers, 
    certificated in any category:
        1. All serial numbers of Models PA24, PA24-250, PA24-260, PA24-
    400, PA30, and PA39 airplanes;
        2. The following model and serial number airplanes that are not 
    equipped with a Piper part number (P/N) 78717-02 main landing gear 
    sidebrace stud in both right and left main landing gear sidebrace 
    bracket assemblies:
    
    ------------------------------------------------------------------------
                    Model                             Serial Nos.           
    ------------------------------------------------------------------------
    PA28R-180...........................  28R-30002 through 28R-31135, and  
                                           28R-7130001 through 28R-7130013. 
    PA28R-200...........................  28R-35001 through 28R-35820, and  
                                           28R-7135001 through 28R-7635539. 
    PA28R-201...........................  28R-7737002 through 28R-7737096.  
    PA28R-201T..........................  28R-7703001 through 28R-7703239.  
    PA32R-300...........................  32R-7680001 through 32R-7780444.  
    PA34-200............................  all serial numbers.               
    PA34-200T...........................  34-7570001 through 34-7770372.    
    ------------------------------------------------------------------------
    
        Note 1: P/N 78717-02 sidebrace stud was installed at manufacture 
    on Piper Model PA34-200T airplanes, serial numbers 34- 7670325 
    through 34-7770372.
        Note 2: This AD applies to each airplane 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 airplanes 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 (e) 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 initially as follows, and thereafter as 
    specified in the body of this AD:
        1. For the affected Models PA28R-180, PA28R-200, PA28R-201, 
    PA28R-201T, PA32R-300, PA34-200, and PA34-200T
    
    [[Page 12]]
    
    airplanes: Within the next 100 hours time-in- service (TIS) after 
    the effective date of this AD or, if the main gear sidebrace stud 
    has already been inspected or replaced as specified in this AD, 
    within 500 hours TIS after the last inspection or replacement, 
    whichever occurs later.
        2. For the affected Models PA24, PA24-250, PA24-260, PA24-400, 
    PA30, and PA39 airplanes: Within the next 100 hours TIS after the 
    effective date of this AD or, if the main gear sidebrace stud has 
    already been inspected or replaced as specified in this AD, within 
    1,000 hours TIS after the last inspection or replacement, whichever 
    occurs later.
        To prevent main landing gear (MLG) collapse caused by main gear 
    sidebrace stud cracks, which could result in loss of control of the 
    airplane during landing operations, accomplish the following:
    
        Note 3: The paragraph structure of this AD is as follows:
    
    Level 1: (a), (b), (c), etc.
    Level 2: (1), (2), (3), etc.
    Level 3: (i), (ii), (iii), etc.
    
        Level 2 and Level 3 structures are designations of the Level 1 
    paragraph they immediately follow.
        (a) Remove both the left and right main gear sidebrace studs 
    from the airplane in accordance with the instructions contained in 
    the Landing Gear section of the maintenance manual, and inspect each 
    main gear sidebrace stud for cracks, using Type I (fluorescent) 
    liquid penetrant or magnetic particle inspection methods. Figure 1 
    of this AD depicts the area of the sidebrace stud shank where the 
    sidebrace stud is to be inspected.
    
        Note 4: All affected Models PA24 and PA24-250 airplanes were 
    equipped at manufacture with P/N 20829-00 main gear sidebrace studs. 
    All affected Models PA24-260, PA24-400, PA30, and PA39 airplanes 
    were equipped at manufacture with P/N 22512-00 main gear sidebrace 
    studs. The Appendix included with this AD contains information on 
    determining the P/N of the bracket assembly (which contains the main 
    gear side brace stud) on the affected PA28R, PA32R, and PA34 series 
    airplanes.
    BILLING CODE 4910-13-U
    
    [[Page 13]]
    
    [GRAPHIC] [TIFF OMITTED] TR02JA97.001
    
    
    BILLING CODE 4910-13-C
    
    [[Page 14]]
    
        (1) For any main gear sidebrace stud found cracked, prior to 
    further flight, replace the cracked stud with an FAA-approved 
    serviceable part (part numbers referenced in the table in paragraph 
    (b) of this AD or FAA-approved equivalent) in accordance with the 
    instructions contained in the Landing Gear section of the applicable 
    maintenance manual, and accomplish one of the following, as 
    applicable:
        (i) Reinspect and replace (as necessary) as specified in 
    paragraph (b) of this AD; or
        (ii) For the affected Models PA28R-180, PA28R-200, PA28R-201, 
    PA28R-201T, PA32R-300, PA34-200, and PA34-200T airplanes, the P/N 
    95299-00 or 95299-02 main gear sidebrace studs are no longer 
    manufactured. Install a new main gear sidebrace stud bracket 
    assembly, P/N 95643-06, P/N 95643-07, P/N 95643-08, or P/N 95643-09, 
    as applicable. No repetitive inspections will be required by this AD 
    for these affected airplane models when this bracket assembly is 
    installed; or
        (iii) For the affected Models PA28R-180, PA28R-200, PA28R-201, 
    PA28R-201T, PA32R-300, PA34-200, and PA34-200T airplanes, ream the 
    existing two-piece bushings, P/N 67026-6, to an inside diameter of 
    .624-inch to .625-inch, chamfer the head side of the bushing to 
    accommodate the radius in the shank of the main gear sidebrace stud, 
    and install the 5/8-inch stud, P/N 78717-02. No repetitive 
    inspections will be required by this AD when this action is 
    accomplished. If the bushings cannot be reamed while installed in 
    the bracket (i.e., the bushings are loose), then install a main gear 
    sidebrace bracket assembly, P/N 95643-06, P/N 95643-07, P/N 95643-
    08, or P/N 95643-09, as applicable. No repetitive inspections will 
    be required by this AD when this bracket assembly is installed.
        (2) For any main gear sidebrace stud not found cracked, prior to 
    further flight, reinstall the uncracked stud in accordance with the 
    instructions contained in the Landing Gear section of the applicable 
    maintenance manual, and reinspect and replace (as necessary) as 
    specified in paragraph (b) of this AD.
        (b) Reinspect both the left and right main gear sidebrace studs, 
    using Type I (fluorescent) liquid penetrant or magnetic particle 
    inspection methods. Replace any cracked stud or reinstall any 
    uncracked stud as specified in paragraphs (a)(1) and (a)(2) of this 
    AD, respectively:
    
    ------------------------------------------------------------------------
                                           TIS                              
                                       inspection  Model airplanes installed
            Part No. installed          interval               on           
                                         (hours)                            
    ------------------------------------------------------------------------
    20829-00 (Piper parts) or FAA-          1,000  PA24 and PA24-250.       
     approved equivalent.                                                   
    22512-00 (Piper parts) or FAA-          1,000  PA24-260, PA24-400, PA30,
     approved equivalent.                           and PA39.               
    95299-00 or 95299-02 (Piper               500  PA28R-180, PA28R-200,    
     parts) or FAA-approved                         PA28R-201, PA28R-201T,  
     equivalent.                                    PA32R-300, PA34-200, and
                                                    PA34-200T.              
    ------------------------------------------------------------------------
    
        Note 5: Accomplishing the actions of this AD does not affect the 
    requirements of AD 77-13-21, Amendment 39-3093. The tolerance 
    inspection requirements of that AD still apply for Piper PA24, PA30, 
    and PA39 series airplanes.
        (c) Owners/operators of the affected Models PA28R-180, PA28R-
    200, PA28R-201, PA28R-201T, PA32R-300, PA34-200, and PA34-200T 
    airplanes may accomplish one of the following at any time to 
    terminate the repetitive inspection requirement of this AD:
        (1) Install a main gear sidebrace bracket assembly, P/N 95643-
    06, P/N 95643-07, P/N 95643-08, or P/N 95643-09, as applicable, 
    which contains the 5/8-inch diameter main gear sidebrace stud, P/N 
    78717-02, and the one-piece bushing, P/N 67026-12; or
        (2) Ream the existing two-piece bushings, P/N 67026-6, to an 
    inside diameter of .624-inch to .625-inch, chamfer the head side of 
    the bushing to accommodate the radius in the shank of the main gear 
    sidebrace stud, and install the 5/8-inch stud, P/N 78717-02. If the 
    bushings cannot be reamed while installed in the bracket (i.e., the 
    bushings are loose), then install a main gear sidebrace bracket 
    assembly, P/N 95643-06, P/N 95643-07, P/N 95643-08, or P/N 95643-09, 
    as applicable.
        (d) 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 airplane to a location where 
    the requirements of this AD can be accomplished.
        (e) An alternative method of compliance or adjustment of the 
    initial or repetitive compliance times that provides an equivalent 
    level of safety may be approved by the Manager, Atlanta Aircraft 
    Certification Office (ACO), Campus Building, 1701 Columbia Avenue, 
    Suite 2-160, College Park, Georgia 30337-2748. The request shall be 
    forwarded through an appropriate FAA Maintenance Inspector, who may 
    add comments and then send it to the Manager, Atlanta ACO. 
    Alternative methods of compliance approved in accordance with AD 95-
    20-07, Amendment 39-9386, are considered approved as alternative 
    methods of compliance with this AD.
    
        Note 6: Information concerning the existence of approved 
    alternative methods of compliance with this AD, if any, may be 
    obtained from the Atlanta ACO.
    
        (f) Information related to this AD may be inspected at the FAA, 
    Central Region, Office of the Assistant Chief Counsel, Room 1558, 
    601 E. 12th Street, Kansas City, Missouri.
        (g) This amendment supersedes AD 95-20-07, Amendment 39-9386.
        (h) This amendment (39-9782) becomes effective on February 7, 
    1997.
    
    Appendix to AD 97-01-01 Information To Determine Main Gear Sidebrace 
    Stud Assembly Part Number (P/N)
    
    --The P/N 95643-00/-01/-02/-03 bracket assembly contains the 9/16-
    inch diameter main gear sidebrace stud, P/N 95299-00/-02, and a two-
    piece bushing, P/N 67026-6.
    --The P/N 95643-06/-07/-08/-09 bracket assembly contains the 5/8-
    inch diameter main gear sidebrace stud, P/N 78717-02, and a one-
    piece bushing, P/N 67026- 12.
    --Both the one-piece and the two-piece bushing have a visible 
    portion of the bushing flange, i.e., bushing shoulder.
    --Whether a one-piece or two-piece bushing is installed may be 
    determined by measuring the outside diameter of the bushing flange 
    with a micrometer (jaws of the caliper must be 3/32-inch or less). 
    The two- piece bushing will have an outside diameter of 1.00 inch 
    and the one-piece bushing will have an outside diameter of 1.128 to 
    1.130 inches. This measurement is not valid for the following 
    airplanes:
    
    ------------------------------------------------------------------------
                    Model                             Serial Nos.           
    ------------------------------------------------------------------------
    PA28R-180...........................  28R-30004 through 28-31270.       
    PA28R-200...........................  28R-35001 through 28R-35820, and  
                                           28R-7135001 through 28R-7135062. 
    ------------------------------------------------------------------------
    
        The main gear sidebrace studs on these airplanes will require 
    removal to determine the P/N installed.
    
    --The one-piece bushing contains a visible chamfer in the center of 
    the bushing, and the chamfer in the two-piece bushing is not visible 
    when the stud is installed.
    --If P/N 95643-00/-01/-02/-03 bracket assembly is installed or the 
    above information cannot be utilized, the main gear sidebrace stud 
    will need to be removed from the bracket to determine the shank 
    diameter and main gear sidebrace stud P/N.
    --P/N 95299-00 and P/N 95299-02 main gear sidebrace studs are \9/
    16\-inch in diameter.
    --P/N 78717-00 main gear sidebrace studs are \5/8\-inch in diameter.
    --P/N 95643-00/-01/-02/-03 bracket assembly may have been modified 
    to accommodate the \5/8\-inch diameter main gear sidebrace stud, P/N 
    78717-02.
    --The embossed number of 95363 on the bracket forging is not the 
    bracket assembly P/N.
    
    
    [[Page 15]]
    
    
        Issued in Kansas City, Missouri, on December 23, 1996.
    Michael Gallagher,
    Manager, Small Airplane Directorate, Aircraft Certification Service.
    [FR Doc. 96-33231 Filed 12-31-96; 8:45 am]
    BILLING CODE 4910-13-U
    
    
    

Document Information

Published:
01/02/1997
Department:
Federal Aviation Administration
Entry Type:
Rule
Action:
Final rule.
Document Number:
96-33231
Dates:
February 7, 1997.
Pages:
10-15 (6 pages)
Docket Numbers:
Docket No. 96-CE-09-AD, Amendment 39-9872, AD 97-01-01
RINs:
2120-AA64: Airworthiness Directives
RIN Links:
https://www.federalregister.gov/regulations/2120-AA64/airworthiness-directives
PDF File:
96-33231.Pdf
CFR: (1)
14 CFR 39.13