[Federal Register Volume 68, Number 62 (Tuesday, April 1, 2003)]
[Rules and Regulations]
[Pages 15653-15657]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-7454]



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  Federal Register / Vol. 68, No. 62 / Tuesday, April 1, 2003 / Rules 
and Regulations  

[[Page 15653]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-CE-37-AD; Amendment 39-13097; AD 2003-07-01]
RIN 2120-AA64


Airworthiness Directives; Quality Aerospace, Inc. S2R Series and 
Model 600 S2D Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment supersedes Airworthiness Directive (AD) 2000-
11-16, which currently applies to certain Quality Aerospace, Inc. 
(Quality Aerospace) (formerly Ayres Corporation) S2R series and Model 
600 S2D airplanes. AD 2000-11-16 requires you to repetitively inspect 
the \1/4\-inch and \5/16\-inch bolt hole areas on the lower spar caps 
for fatigue cracking; replace or repair any lower spar cap where 
fatigue cracking is found; and report any fatigue cracking found. AD 
2000-11-16 resulted from an accident of an Ayres S2R series airplane 
where the wing separated from the airplane in flight. Since AD 2000-11-
16, additional airplanes have been identified that were manufactured 
with a similar design to those affected by the AD and a third repair 
option has been developed. This AD retains the repetitive inspections 
and replacement (if necessary) requirements of the lower spar caps that 
are currently required in AD 2000-11-16, adds additional airplanes to 
the Applicability of the AD, and adds a third repair option. The 
actions specified by this AD are intended to detect and correct fatigue 
cracking of the lower spar caps, which could result in the wing 
separating from the airplane with consequent loss of control of the 
airplane.

DATES: This AD becomes effective on May 20, 2003.
    The Director of the Federal Register previously approved the 
incorporation by reference of Ayres Service Bulletin No. SB-AG-39, 
dated September 17, 1996; Ayres Custom Kit No. CK-AG-29, dated December 
23, 1997, as of July 25, 2000 (65 FR 36055, June 7, 2000).
    The Director of the Federal Register approved the incorporation by 
reference of Quality Aerospace, Inc. Custom Kit No. CK-AG-30, dated 
December 6, 2001, as of May 20, 2003.

ADDRESSES: You may get the service information referenced in this AD 
from Quality Aerospace, Inc., P.O. Box 3050, Albany, Georgia 31706-
3050; telephone: (229) 883-1440; facsimile: (229) 883-9790. You may 
view this information at the Federal Aviation Administration (FAA), 
Central Region, Office of the Regional Counsel, Attention: Rules Docket 
No. 2001-CE-37-AD, 901 Locust, Room 506, 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: Cindy Lorenzen, Aerospace Engineer, 
FAA, Aircraft Certification Office, One Crown Center, 1895 Phoenix 
Boulevard, suite 450, Atlanta, Georgia 30349; telephone: (770) 703-
6078; facsimile: (770) 703-6097.

SUPPLEMENTARY INFORMATION:

Discussion

What Events Have Caused This AD?

    An accident on an Ayres S2R series airplane where the wing 
separated from the airplane in flight caused us to issue AD 2000-11-16, 
Amendment 39-11764 (65 FR 36055, June 7, 2000). This AD requires the 
following on certain Quality Aerospace S2R series and Model 600 S2D 
airplanes:
    [sbull] Repetitively inspect the \1/4\-inch and \5/16\-inch bolt 
hole areas on the lower spar caps for fatigue cracking;
    [sbull] Replacing or repairing any lower spar cap where fatigue 
cracking is found; and
    [sbull] Reporting any fatigue cracking to FAA.
    AD 2000-11-16 superseded AD 97-17-03, Amendment 39-10195 (62 FR 
43296, August 18, 1997), which required accomplishing the following:
    [sbull] Inspecting the \1/4\-inch and \5/16\-inch bolt hole areas 
on the lower spar caps for fatigue cracking;
    [sbull] Replacing any lower spar cap where fatigue cracking is 
found; and
    [sbull] Reporting any fatigue cracking to FAA.
    AD 2000-11-16 made the inspections required in AD 97-17-03 
repetitive, added additional airplanes to the Applicability of the AD, 
changed the initial compliance time for all airplanes, and arranged the 
affected airplanes into six groups based on usage and configuration.
    AD 97-17-03 superseded AD 97-13-11, Amendment 39-10071 (62 FR 
36978, July 10, 1997), which required accomplishing the following:
    [sbull] Inspecting the \1/4\-inch and \5/16\-inch bolt hole areas 
on the lower spar caps for fatigue cracking;
    [sbull] Replacing any lower spar cap where fatigue cracking is 
found; and
    [sbull] Reporting any fatigue cracking to FAA.
    AD 97-13-11 incorrectly referenced the Ayres Model S2R-R1340 
airplanes as Model S2R-1340R. AD 97-17-03 corrected the model 
designation and retained the actions of AD 97-13-11.

What Has Happened Since AD 2000-11-16 To Initiate This Action?

    Since AD 2000-11-16, FAA has identified additional airplanes with 
the same type design that should be added to the Applicability of the 
AD. The manufacturer has issued update service information that gives 
the owners/operators of the affected airplanes an additional repair 
option. We have also identified several minor typographical errors in 
AD 2000-11-16.

What Is the Potential Impact if FAA Took No Action?

    This condition, if not corrected, could result in the wing 
separating from the airplane with consequent loss of control of the 
airplane.

Has FAA Taken Any Action to This Point?

    We issued a proposal to amend part 39 of the Federal Aviation 
Regulations (14 CFR part 39) to include an AD that would apply to 
certain Quality Aerospace (formerly Ayres Corporation) S2R series and 
Model 600 S2D airplanes. This proposal was published in the Federal 
Register as a notice of proposed rulemaking (NPRM) on

[[Page 15654]]

November 8, 2002 (67 FR 68047). The NPRM proposed to supersede AD 2000-
11-16 with a new AD that would:
    [sbull] Retain the repetitive inspections and replacement (if 
necessary) requirements of AD 2000-11-16;
    [sbull] Add an additional repair option of installing a splice 
block to improve the chances of salvaging a spar cap that has small 
cracks in the \1/4\-inch and \5/16\-inch bolt holes; and
    [sbull] Add additional airplanes to the Applicability of the AD.

Was the Public Invited To Comment?

    The FAA encouraged interested persons to participate in the making 
of this amendment. The following presents the comments received on the 
proposal and FAA's response to each comment:

Comment Issue: Reference Correct Standard for Magnetic Particle 
Inspection

What Is the Commenter's Concern?

    One commenter states that the American Society for Testing 
Materials (ASTM) Standard referenced in the proposed AD, ASTM Standard 
E 1444-94A, should be changed to the updated ASTM Standard E 1444-01. 
The standard has been updated by the ASTM and the document referenced 
in the NPRM is outdated.

What Is FAA's Response to the Concern?

    We concur with the commenter and will change the final rule AD 
action to incorporate this change.

FAA's Determination

What Is FAA's Final Determination on This Issue?

    We carefully reviewed all available information related to the 
subject presented above and determined that air safety and the public 
interest require the adoption of the rule as proposed except for the 
reference change discussed above and minor editorial corrections. We 
have determined that these changes and minor corrections:
    [sbull] Provide the intent that was proposed in the NPRM for 
correcting the unsafe condition; and
    [sbull] Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Cost Impact

How Many Airplanes Does This AD Impact?

    We estimate that this AD affects 1,015 airplanes in the U.S. 
registry.

What Is the Cost Impact of This AD on Owners/Operators of the Affected 
Airplanes?

    We estimate the following costs to accomplish each inspection:

----------------------------------------------------------------------------------------------------------------
                                                    Total cost per
            Labor cost                Parts cost       airplane             Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
3 workhours x $60 = $180..........            $417            $597  1,015 x $597 = $605,955.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to accomplish any necessary cold 
work of bolt holes that will be required based on the results of the 
inspection. We have no way of determining the number of airplanes that 
may need such repair:

------------------------------------------------------------------------
                                                          Total cost per
               Labor cost                   Parts cost       airplane
------------------------------------------------------------------------
1 workhour x $60 = $60..................            $100            $160
------------------------------------------------------------------------

    We estimate the following costs to accomplish any necessary 
installation of a butterfly splice plate that will be required based on 
the results of the inspection. We have no way of determining the number 
of airplanes that may need such installation:

------------------------------------------------------------------------
                                                          Total cost per
               Labor cost                   Parts cost       airplane
------------------------------------------------------------------------
70 workhours x $60 = $4,200.............            $700          $4,900
------------------------------------------------------------------------

    We estimate the following costs to accomplish any necessary reaming 
of outer holes to \5/16\-inch diameter that will be required based on 
the results of the inspection. We have no way of determining the number 
of airplanes that may need such repair:

------------------------------------------------------------------------
                                                          Total cost per
               Labor cost                   Parts cost       airplane
------------------------------------------------------------------------
1 workhour x $60 = $60..................            None             $60
------------------------------------------------------------------------

    We estimate the following costs to accomplish any necessary 
drilling and reaming of outer holes and adding three holes to install a 
splice block that will be required based on the results of the 
inspection. We have no way of determining the number of airplanes that 
may need such modification:

------------------------------------------------------------------------
                                                          Total cost per
               Labor cost                   Parts cost       airplane
------------------------------------------------------------------------
65 workhours x $60 = $3,900.............          $4,100          $8,000
------------------------------------------------------------------------


[[Page 15655]]

    We estimate the following costs to accomplish any necessary spar 
cap replacement that will be required based on the results of the 
inspection. We have no way of determining the number of airplanes that 
may need such replacement:

------------------------------------------------------------------------
                                          Parts cost per  Total cost per
         Labor cost per spar cap             spar cap        spar cap
------------------------------------------------------------------------
200 workhours x $60 = $12,000...........          $2,316         $14,316
------------------------------------------------------------------------

What Is the Difference Between the Cost Impact of This AD and the Cost 
Impact of AD 2000-11-16?

    The differences between this AD and the cost impact of AD 2000-11-
16 are:
    [sbull] The addition of an optional repair to install a splice 
block; and
    [sbull] The addition of 15 airplanes of similar design.

Regulatory Impact

Does This AD Impact Various Entities?

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.

Does This AD Involve a Significant Rule or Regulatory Action?

    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

0
Accordingly, under 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

0
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]

0
2. FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2000-11-16, Amendment 39-11764 (65 FR 36055, June 7, 2000), and by 
adding a new AD to read as follows:

2003-07-01 Quality Aerospace, Inc. (Ayres Corporation formerly held 
Type Certificate (TC) No. A4SW): Amendment 39-13097; Docket No. 
2001-CE-37-AD; Supersedes AD 2000-11-16, Amendment 39-11764.

    (a) What airplanes are affected by this AD? This AD affects the 
following airplane models and serial numbers that are certificated 
in any category and do not incorporate a P/N 22507 lower spar cap on 
both the left and right wings:

------------------------------------------------------------------------
             Model                     Serial Nos.             Group
------------------------------------------------------------------------
(1) S-2R.......................  5000R through 5099R,                  1
                                  except 5010R, 5031R,
                                  5038R, 5047R, and
                                  5085R.
(2) S2R-G1.....................  G1-101 through G1-106..               1
(3) S2R-R1820..................  R1820-001 through R1820-              1
                                  035.
(4) S2R-T15....................  T15-001 through T15-033               1
(5) S2R-T34....................  6000R through 6049R,                  1
                                  T34-001 through T34-
                                  143, T34-145, T34-147
                                  through T34-167, T34-
                                  171, T34-180, and T34-
                                  181.
(6) S2R-G10....................  G10-101 through G10-                  2
                                  136, G10-138, G10-140,
                                  and G10-141.
(7) S2R-G5.....................  G5-101 through G5-105..               2
(8) S2R-G6.....................  G6-101 through G6-147..               2
(9) S2RHG-T65..................  T65-002 through T65-018               2
(10) S2R-R1820.................  R1820-036..............               2
(11) S2R-T34...................  T34-144, T34-146, T34-                2
                                  168, T34-169, T34-172
                                  through T34-179, and
                                  T34-189 through T34-
                                  232, and T34-234.
(12) S2R-T45...................  T45-001 through T45-014               2
(13) S2R-T65...................  T65-001 through T65-018               2
(14) 600 S2D...................  All serial numbers                    3
                                  beginning with 600-
                                  1311D.
(15) S-2R......................  1380R and 1416R through               3
                                  2592R.
(16) S2R-R1340.................  R1340-001 through R1340-              3
                                  035.
(17) S2R-R3S...................  R3S-001 through R3S-011               3
(18) S2R-T11...................  T11-001 through T11-005               3
(19) S2R-G1....................  G1-107, G1-108, and G1-               4
                                  109.
(20) S2R-G10...................  G10-137, G10-139, and                 4
                                  G10-142.
(21) S2R-T34...................  T34-236, T34-237, and                 4
                                  T34-238.
(22) S2R-G1....................  G1-110 through G1-115..               5
(23) S2R-G10...................  G10-143 through G10-165               5
(24) S2R-G6....................  G6-148 through G6-155..               5
(25) S2RHG-T34.................  T34HG-101 and T34HG-102               5
(26) S2R-T15...................  T15-034 through T15-040               5
(27) S2R-T34...................  T34-239 through T34-270               5
(28) S2R-T45...................  T45-015................               5
(29) S2R.......................  5010R, 5031R, 5038R,                  6
                                  5047R, and 5085R.
------------------------------------------------------------------------



[[Page 15656]]

    Note 1: The serial numbers of the Model S2R-T15 airplanes could 
incorporate T15-xxx and T27-xxx. This AD applies to both of these 
serial number designations as they are both Model S2R-T15 airplanes.


    Note 2: The serial numbers of the Model S2R-T34 airplanes could 
incorporate T34-xxx, T36-xxx, T41-xxx, or T42-xxx. This AD applies 
to all of these serial number designations as they are all Model 
S2R-T34 airplanes.


    Note 3: Any Group 3 airplane that has been modified with a 
hopper of a capacity more than 410 gallons, a piston engine greater 
than 600 horsepower, or any gas turbine engine, makes the airplane a 
Group 1 airplane for the purposes of this AD. Inspect the airplane 
at the Group 1 compliance time specified in this AD.

    (b) Who must comply with this AD? Anyone who wishes to operate 
any of the airplanes identified in paragraph (a) of this AD must 
comply with this AD.
    (c) What problem does this AD address? The actions specified by 
this AD are intended to detect and correct fatigue cracking of the 
lower spar caps, which could result in the wing separating from the 
airplane with consequent loss of control of the airplane.
    (d) What actions must I accomplish to address this problem? To 
address this problem, you must accomplish the following:
    (1) Repetitively inspect, using magnetic particle, ultrasonic, 
or eddy current procedures, the \1/4\-inch and \5/16\-inch bolt hole 
areas on each lower spar cap for fatigue cracking. Reference 
paragraph (e)(3) and (e)(4) of this AD (including all subparagraphs) 
to obtain the initial and repetitive inspection compliance times.
    (i) The cracks may emanate from the bolt hole on the face of the 
spar cap or they may occur in the shaft of the hole.
    (ii) You must inspect both of these areas.
    (iii) If using the magnetic particle method for the inspection, 
perform the inspection using the ``Inspection'' portion of the 
``Accomplishment Instructions'' and ``Lower Splice Fitting Removal 
and Installation Instructions'' in Ayres Service Bulletin No. SB-AG-
39, dated September 17, 1996. You must follow American Society for 
Testing Materials (ASTM) E 1444-01, using wet particles meeting the 
requirements of the Society for Automotive Engineers (SAE) AMS 3046. 
The inspection must be performed by or supervised by a Level 2 or 
Level 3 inspector certified for magnetic particle inspection method 
using the guidelines established by the American Society for 
Nondestructive Testing or MIL-STD-410. CAUTION: You must firmly 
support the wings during the inspection to prevent movement of the 
spar caps when the splice blocks are removed. This will allow easier 
realignment of the splice block holes and the holes in the spar cap 
for bolt insertion.
    (iv) If using ultrasonic or eddy current methods for the 
inspection, a procedure must be sent to the FAA Atlanta Aircraft 
Certification Office (ACO) for approval prior to performing the 
inspection. Send your proposed procedure to the FAA Atlanta Aircraft 
ACO, Attn: Cindy Lorenzen, One Crown Center, 1895 Phoenix Boulevard, 
Suite 450, Atlanta, Georgia 30349. You are not required to remove 
the splice block for either the ultrasonic or eddy current 
inspections, unless corrosion is visible.
    (2) If any cracking is found during any inspection required by 
this AD, you must accomplish the following:
    (i) Repair or replace:
    (A) Use the cold work process to ream out small cracks as 
defined in Ayres Service Bulletin No. SB-AG-39, dated September 17, 
1996; or
    (B) Ream the \1/4\-inch bolt holes to \5/16\ inches diameter as 
defined in Part I of Ayres Custom Kit No. CK-AG-29, dated December 
23, 1997; or
    (C) Install Kaplan Splice Blocks as defined in Quality 
Aerospace, Inc. Custom Kit No. CK-AG-30, dated December 6, 2001; or
    (D) Replace the affected spar cap in accordance with the 
maintenance manual.
    (ii) Submit a report of inspection findings to the Manager, 
Atlanta ACO, One Crown Center, 1895 Phoenix Boulevard, Suite 450, 
Atlanta, Georgia 30349; facsimile: (770) 703-6097. You must include:
    (A) The airplane serial number and engine model number;
    (B) The total number of flight hours on the lower spar cap that 
is cracked;
    (C) Time on the spar cap since last inspection, if applicable;
    (D) The procedure (magnetic particle, ultrasonic, or eddy 
current) used for the last inspection;
    (E) Indicate if cold working has been accomplished or 
modifications incorporated such as installation of big butterfly 
plates;
    (F) Indicate the time on the spar cap when the cold working or 
modifications were accomplished; and
    (G) Indicate which bolt hole is cracked and the length of the 
crack.

    Note 4: Information collection requirements contained in this 
regulation have been approved by the Office of Management and Budget 
(OMB) under the provisions of the Paperwork Reduction Act of 1980 
(44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 
2120-0056.

    (e) What is the compliance time of this AD? The compliance times 
for each of the actions of this AD are as follows:
    (1) Any required repair or replacement: Prior to further flight 
after the inspection where the crack(s) was/were found.
    (2) Reporting requirement:
    (i) Submit the report within 10 days after finding any crack(s) 
during any inspection required by this AD.
    (ii) For airplanes where cracking was found during any 
inspection accomplished in accordance with AD 2000-11-16, which is 
superseded by this AD; or by AD 97-17-03, which was superseded AD 
2000-11-16; or by AD 97-13-11, which was superseded by AD 97-17-03, 
submit the report within 10 days after May 20, 2003 (the effective 
date of this AD), unless already accomplished.
    (3) Initial inspection: Required unless already accomplished 
(compliance with AD 2000-11-16, or AD 97-17-03, or AD97-13-11) 
within 50 flight hours after May 20, 2003 (the effective date of 
this AD) or upon the accumulation of these hours time-in-service 
(TIS) on each lower spar cap, whichever occurs later:

------------------------------------------------------------------------
           Airplane group                  Lower spar cap hours TIS
------------------------------------------------------------------------
(i) 1...............................  2,000
(ii) 2..............................  2,200
(iii) 3.............................  6,400
(iv) 4..............................  2,500
(v) 5...............................  6,200
(vi) 6:
                                      For S/N 5010R: 5,530
                                      For S/N 5038R: 5,900
                                      For S/N 5031R: 6,400
                                      For S/N 5047R: 6,400
                                      For S/N 5085R: 6,290
------------------------------------------------------------------------

    (4) Repetitive inspections: The following table gives the 
required repetitive inspection intervals based on the work performed 
and the method of inspection utilized. Each time is hours TIS after 
the last inspection:

----------------------------------------------------------------------------------------------------------------
                                                                     Magnetic
                    Work previously performed                     particle hours    Ultrasonic     Eddy current
                                                                        TIS          hours TIS       hours TIS
----------------------------------------------------------------------------------------------------------------
(i) One of the following where the airplane does not have                    500             550             700
 butterfly plates, part number (P/N) 20211-09 and P/N 20211-11,
 installed per CK-AG-29, Part II................................
    (A) No cracks found previously on wing spar; or
    (B) Small cracks repaired through cold work (or done as an
     option if never cracked) accomplished per SB-AG-39; or
    (C) Small cracks repaired through \1/4\-inch bolt hole
     reamed to \5/16\ inch diameter (or done as an option if
     never cracked) per CK-AG-29, Part I; or
    (D) Small cracks repaired through previous Alternative
     Methods of Compliance; or
    (E) Small cracks repaired by installation of Kaplan Splice
     Blocks, part number 22515-1-3 or 88-251 (or done as an
     option if never cracked) per CK-AG-30 and inspection of the
     six outboard bolt holes on both lower spars is required
(ii) One of the following where the airplane has butterfly                   900             950           1,250
 plates, part number (P/N) 20211-09 and P/N 20211-11, installed
 per CK-AG-29, Part II..........................................
    (A) No cracks found previously on wing spar; or

[[Page 15657]]

 
    (B) Small cracks repaired through cold work (or done as an
     option if no cracks found) accomplished per SB-AG-39; or
    (C) Small cracks repaired through \1/4\-inch bolt hole
     reamed to \5/16\ inch diameter (or done as an option if no
     cracks found) per CK-AG-29, Part I; or
    (D) Small cracks repaired through previous Alternative
     Methods of Compliance; or
    (E) Small cracks repaired by installation of Kaplan Splice
     Blocks, part number 22515-1-3 or 88-251 (or done as an
     option if never cracked) per CK-AG-30 and inspection of the
     six outboard bolt holes on both lower spar caps is required
(iii) Cracked wing spar found during previous inspection with
 wing spar replacement..........................................  For all inspection methods (magnetic particle,
                                                                  ultrasonic, or eddy current), time for initial
                                                                  and repetitive inspection intervals start over
                                                                  when wing spar is replaced.
----------------------------------------------------------------------------------------------------------------


    Note 5: Aircraft S/Ns T45-007DC and T45-010DC had modified 
splice block assemblies installed at Ayres (Ayres/Kaplan Assembly 
No. 88-251) and must still follow the repetitive inspection 
intervals listed here.


    Note 6: If a crack is found, the reaming associated with the 
cold work process may remove a crack if it is small enough. Some 
aircraft owners/operators were issued alternative methods of 
compliance with AD 97-17-03 to ream the \1/4\-inch bolt hole to \5/
16\ inch diameter to remove small cracks. Ayres CK-AG-29, Part I, 
also provides procedures to ream the \1/4\-inch bolt hole to \5/16\ 
inch diameter. If you use either of these two methods to remove 
cracks and the airplane is reinspected immediately with no cracks 
found, you may continue to follow the repetitive inspection 
intervals listed above.


    Note 7: Group 4 and Group 5 airplanes had the butterfly plates 
installed at the factory and may follow the repetitive inspection 
interval listed in paragraph (e)(4)(ii).

    (f) Can I comply with this AD in any other way?
    (1) You may use an alternative method of compliance or adjust 
the compliance time if:
    (i) Your alternative method of compliance provides an equivalent 
level of safety; and
    (ii) The Manager, Atlanta ACO, approves your alternative. Submit 
your request through an FAA Principal Maintenance Inspector, who may 
add comments and then send it to the Manager, Atlanta ACO.
    (2) Alternative methods of compliance approved in accordance 
with AD 2000-11-16, which is superseded by this AD, are approved as 
alternative methods of compliance with this AD.

    Note 8: This AD applies to each airplane identified in paragraph 
(a) of this AD, 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 (f) 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 you have not eliminated the unsafe condition, specific 
actions you propose to address it.

    (g) Where can I get information about any already-approved 
alternative methods of compliance? Contact Cindy Lorenzen, Aerospace 
Engineer, FAA, Aircraft Certification Office, One Crown Center, 1895 
Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; telephone: 
(770) 703-6078; facsimile: (770) 703-6097.
    (h) What if I need to fly the airplane to another location to 
comply with this AD? The FAA can issue a special flight permit under 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate your airplane to a location where 
you can accomplish the requirements of this AD provided that:
    (1) the hopper is empty;
    (2) Vne is reduced to 126 miles per hour (109 knots) indicated 
airspeed (IAS); and
    (3) flight into known turbulence is prohibited.
    (i) Are any service bulletins incorporated into this AD by 
reference?
    (1) Actions required by this AD must be done in accordance with 
Ayres Service Bulletin No. SB-AG-39, dated September 17, 1996; Ayres 
Custom Kit No. CK-AG-29, dated December 23, 1997; and Quality 
Aerospace, Inc. Custom Kit No. CK-AG-30, dated December 6, 2001.
    (i) The Director of the Federal Register approved the 
incorporation by reference of Quality Aerospace, Inc. Custom Kit No. 
CK-AG-30, dated December 6, 2001, under 5 U.S.C. 552(a) and 1 CFR 
part 51. You may get copies from Quality Aerospace, Inc., P.O. Box 
3050, Albany, Georgia 31706-3050; telephone: (229) 883-1440; 
facsimile: (229) 883-9790.
    (ii) The Director of the Federal Register previously approved 
the incorporation by reference of Ayres Service Bulletin No. SB-AG-
39, dated September 17, 1996; Ayres Custom Kit No. CK-AG-29, dated 
December 23, 1997, as of July 25, 2000 (65 FR 36055, June 7, 2000).
    (2) You may get copies from Quality Aerospace, Inc., P.O. Box 
3050, Albany, Georgia 31706-3050; telephone: (229) 883-1440; 
facsimile: (229) 883-9790. You may view copies at the FAA, Central 
Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas 
City, Missouri, or at the Office of the Federal Register, 800 North 
Capitol Street, NW, suite 700, Washington, DC.
    (j) Does this AD action affect any existing AD actions? This 
amendment supersedes AD 2000-11-16, Amendment 39-11764.
    (k) When does this amendment become effective? This amendment 
becomes effective on May 20, 2003.

    Issued in Kansas City, Missouri, on March 21, 2003.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-7454 Filed 3-31-03; 8:45 am]
BILLING CODE 4910-13-P