[Federal Register Volume 69, Number 82 (Wednesday, April 28, 2004)]
[Rules and Regulations]
[Pages 23093-23095]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-9380]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-65-AD; Amendment 39-13594; AD 2004-09-05]
RIN 2120-AA64


Airworthiness Directives; Cessna Model 500, 501, 550, and 551 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD); 
applicable to certain Cessna Model 500, 501, 550, and 551 airplanes; 
that requires a one-time inspection of the brake stator disks to 
determine to what change level they have been modified (if any), and 
related investigative and corrective actions if necessary. This AD also 
requires that the existing markings on the piston housing of certain 
brake assemblies be eliminated. The actions specified by this AD are 
intended to prevent wheel lockups that may be caused by cracked or 
broken brake stator disks becoming jammed in the brake assembly and 
preventing rotation. Such jamming of the brake assembly may result in 
reduced directional control or braking performance during landing. This 
action is intended to address the identified unsafe condition.

DATES: Effective June 2, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 2, 2004.

ADDRESSES: The service information referenced in this AD may be 
obtained from Cessna Aircraft Co., P.O. Box 7706, Wichita, Kansas 
67277. This information may be examined at the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, Rules Docket, 
1601 Lind Avenue, SW., Renton, Washington; at the FAA, Wichita Aircraft 
Certification Office, 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: David Hirt, Aerospace Engineer, 
Systems and Propulsion Branch, ACE-116W, Wichita Aircraft Certification 
Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, 
Kansas 67209; telephone (316) 946-4156; fax (316) 946-4407.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Cessna Model 500, 501, 
550, and 551 airplanes was published as a supplemental notice of 
proposed rulemaking (NPRM) in the Federal Register on November 12, 2003 
(68 FR 64002). That action proposed to require a one-time inspection of 
the brake stator disks to determine to what change level they have been 
modified (if any), and follow-on actions if necessary. That action also 
proposed to require that the existing markings on the piston housing of 
certain brake assemblies be eliminated.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Request To Withdraw NPRM

    One commenter, the manufacturer of the subject brake assemblies, 
requests that the FAA withdraw the NPRM because the proposed AD is not 
timely and would place an unnecessary cost burden on operators. The 
commenter states that the average service life of the subject brake 
assemblies is 592 landings. With a utilization rate of 20 landings per 
month, the service life is approximately 30 months. Based on this 
information, and considering the date of issuance of the Goodrich 
service bulletins and the distribution of brake stator disks with 
change-level ``B,'' the commenter estimates that the subject brake 
stator disks should have been retired from service by July 2002. The 
commenter states that the proposed AD will have a negative economic 
effect on subject operators by subjecting them to an inspection for a 
component change letter range that should have been removed from 
service more than 17 months ago.
    We do not concur. The information supplied by the commenter does 
not address the fact that this unsafe condition may still be present on 
airplanes that are operated at a utilization rate that is lower than 
average, or defective brakes in spares stocks that may be installed on 
airplanes in the future. The commenter also does not address the 
possibility that certain operators may have chosen not to comply with 
the actions in the Goodrich service bulletins referenced in this AD. We 
find that it is necessary to proceed with this AD to ensure that all 
subject stator disks are inspected in a timely manner. No change to the 
AD is necessary in this regard.

Explanation of Additional Changes to Final Rule

    Paragraphs (d) and (e) of the supplemental NPRM state, ``If 
repetitive inspections are required by paragraph (c) of this AD, 
[replacement of the brake assembly with a new or serviceable brake 
assembly] terminates those inspections.'' We find that this statement 
may potentially cause confusion related to the inspection requirements 
specified in paragraph (f) of this AD. It was not our intent for the 
terminating action statement included in paragraphs (d) and (e) of this 
AD to terminate inspections that may be required by paragraph (f) of 
this AD. For clarification, we have revised paragraphs (d) and (e) of 
this final rule to state that, if repetitive inspections are required 
by paragraph (c) of this AD, repetitive inspections are terminated 
after all brake assemblies on the airplane contain only stator disks 
stamped with ``CHG AI'' or ``CHG B'' or a higher change letter. Related 
to this change, we have also revised paragraph (f) of this AD to 
clarify that the actions in paragraph (c) of this AD, which contains 
follow-on actions to paragraph (b) of this AD, must be accomplished 
when applicable.
    Also, we have revised the Summary section of this final rule to 
change the term ``follow-on actions'' to ``related investigative and 
corrective actions.'' We find that this wording better describes the 
actions that are required for any stator disk not stamped with ``CHG 
AI'' or ``CHG B'' or a higher change letter.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air

[[Page 23094]]

safety and the public interest require the adoption of the rule with 
the changes previously described. The FAA has determined that these 
changes will neither increase the economic burden on any operator nor 
increase the scope of the AD.

Cost Impact

    There are approximately 370 airplanes of the affected design in the 
worldwide fleet. We estimate that 259 airplanes of U.S. registry will 
be affected by this AD. It will take up to 1 work hour per airplane to 
accomplish the required inspection if the inspection were done at the 
time of a tire change and up to 4 work hours per airplane if the 
inspection were done at a different time, at an average labor rate of 
$65 per work hour. Based on these figures, the cost impact of this AD 
on U.S. operators is estimated to be $16,835, or $65 per airplane, for 
inspections of the brake assembly done at the time of a tire change; or 
up to $67,340, or $260 per airplane, for inspections done at a 
different time.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    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.
    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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
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

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. Section 39.13 is amended by adding the following new airworthiness 
directive:

2004-09-05 Cessna Airplane Company: Amendment 39-13594. Docket 2000-
NM-65-AD.

    Applicability: Model 500 and 501 airplanes, serial numbers 0001 
through 0689 inclusive, and Model 550 and 551 airplanes, serial 
numbers 0002 through 0733 inclusive; certificated in any category; 
equipped with BFGoodrich brake assembly part number (P/N) 2-1528-6 
or 2-1530-4.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent jamming of the wheel/tire assembly, which could 
result in a loss of directional control or braking performance upon 
landing, accomplish the following:

Inspection of Stator Disks for Change Letter

    (a) Within 50 landings or 90 days after the effective date of 
this AD, whichever is first, inspect the stator disks on the brake 
assembly to determine if ``CHG AI'' or ``CHG B'' or a higher change 
letter is impression-stamped on each disk, in accordance with 
Goodrich Service Bulletin 2-1528-32-2 (for airplanes equipped with 
BFGoodrich brake assembly P/N 2-1528-6); or Goodrich Service 
Bulletin 2-1530-32-2 (for airplanes equipped with BFGoodrich brake 
assembly P/N 2-1530-4); both Revision 5; both dated February 19, 
2003; as applicable. If both disks are stamped with ``CHG AI'' or 
``CHG B'' or a higher change letter, no further action is required 
by this paragraph. A review of airplane maintenance records is 
acceptable in lieu of an inspection of the stator disks if the 
change letter of the stator disks can be positively determined from 
that review.

Inspection for Cracked or Broken Stator Disks

    (b) For any stator disk not stamped with ``CHG AI'' or ``CHG B'' 
or a higher change letter: At the applicable compliance time 
specified in paragraph (b)(1) or (b)(2) of this AD, perform a 
detailed inspection for cracked or broken stator disks; in 
accordance with Goodrich Service Bulletin 2-1528-32-2 (for airplanes 
equipped with BFGoodrich brake assembly P/N 2-1528-6); or Goodrich 
Service Bulletin 2-1530-32-2 (for airplanes equipped with BFGoodrich 
brake assembly P/N 2-1530-4); both Revision 5; both dated February 
19, 2003; as applicable.
    (1) For airplanes that use thrust reversers: Inspect prior to 
the accumulation of 376 total landings on the brake assembly, or 
within 50 landings after the effective date of this AD, whichever is 
later.
    (2) For airplanes that do not use thrust reversers: Inspect 
prior to the accumulation of 200 total landings on the brake 
assembly, or within 25 landings after the effective date of this AD, 
whichever is later.

    Note 1: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''

Follow-On Actions (No Cracked or Broken Stator Disk)

    (c) If no cracked or broken stator disk is found, before further 
flight, reassemble the brake assembly and, if the piston housing is 
impression-stamped with the letters ``SB,'' obliterate the existing 
markings on the piston housing by stamping ``XX'' over the letters 
``SB.'' If paragraph E.(3)(a) or E.(3)(b), as applicable, of 
Goodrich Service Bulletin 2-1528-32-2 (for airplanes equipped with 
BFGoodrich brake assembly P/N 2-1528-6); or Goodrich Service 
Bulletin 2-1530-32-2 (for airplanes equipped with BFGoodrich brake 
assembly P/N 2-1530-4); both Revision 5; both dated February 19, 
2003; as applicable; specifies repetitive inspections, repeat the 
inspection required by paragraph (b) of this AD at intervals not to 
exceed those specified in the service bulletin, until paragraph (e) 
of this AD is accomplished.

Corrective Action (Cracked or Broken Stator Disk)

    (d) If any cracked or broken stator disk is found, prior to 
further flight, replace the brake assembly with a new or serviceable 
brake assembly; in accordance with Goodrich Service Bulletin 2-1528-
32-2 (for airplanes equipped with BFGoodrich brake assembly P/N 2-
1528-6); or Goodrich Service Bulletin 2-1530-32-2 (for airplanes 
equipped with BFGoodrich brake assembly P/N 2-1530-4); both Revision 
5; both dated February 19, 2003; as applicable. If repetitive 
inspections are required by paragraph (c) of this AD, replacement of 
all brake assemblies on the airplane with new or serviceable brake 
assemblies that contain only stator disks stamped with ``CHG AI'' or 
``CHG B'' or a higher change letter terminates those inspections.

[[Page 23095]]

Replacement of Brake Assembly

    (e) When the brake assembly has accumulated 700 total landings 
since its installation or within 50 landings on the airplane after 
the effective date of this AD, whichever is later, replace the brake 
assembly with a new or serviceable brake assembly; in accordance 
with Goodrich Service Bulletin 2-1528-32-2 (for airplanes equipped 
with BFGoodrich brake assembly P/N 2-1528-6); or Goodrich Service 
Bulletin 2-1530-32-2 (for airplanes equipped with BFGoodrich brake 
assembly P/N 2-1530-4); both Revision 5; both dated February 19, 
2003; as applicable. If repetitive inspections are required by 
paragraph (c) of this AD, replacement of all brake assemblies on the 
airplane with new or serviceable brake assemblies that contain only 
stator disks stamped with ``CHG AI'' or ``CHG B'' or a higher change 
letter terminates those inspections.

Parts Installation

    (f) As of the effective date of this AD, no person may install a 
BFGoodrich brake assembly on any airplane unless it has been 
inspected as specified in paragraph (f)(1) or (f)(2) of this AD, and 
found to be free of cracked or broken stator disks.
    (1) For BFGoodrich brake assembly P/N 2-1528-6: Brake assembly 
must be inspected in accordance with paragraphs (a), (b), and (c) of 
this AD, as applicable, in accordance with the service information 
specified in those paragraphs or BFGoodrich Service Bulletin 2-1528-
32-3, dated March 23, 2000.
    (2) For BFGoodrich brake assembly P/N 2-1530-4: Brake assembly 
must be inspected in accordance with paragraphs (a), (b), and (c) of 
this AD, as applicable, in accordance with the service information 
specified in those paragraphs or BFGoodrich Service Bulletin 2-1530-
32-3, dated March 23, 2000.

Alternative Methods of Compliance

    (g) In accordance with 14 CFR 39.19, the Manager, Wichita 
Aircraft Certification Office (ACO), FAA, is authorized to approve 
alternative methods of compliance for this AD.

Incorporation by Reference

    (h) Unless otherwise specified in this AD, the actions shall be 
done in accordance with the applicable service bulletin listed in 
Table 1 of this AD.

          Table 1.--Service Bulletins Incorporated by Reference
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       Service bulletin            Revision                Date
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BFGoodrich Service Bulletin 2- Original........  March 23, 2000.
 1528-32-3.
BFGoodrich Service Bulletin 2- Original........  March 23, 2000.
 1530-32-3.
Goodrich Service Bulletin 2-   5...............  February 19, 2003.
 1528-32-2.
Goodrich Service Bulletin 2-   5...............  February 19, 2003.
 1530-32-2.
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    Goodrich Service Bulletin 2-1528-32-2, Revision 5, contains the 
following effective pages:

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                                Revision level
         Page  number            show on page      Date  shown on page
------------------------------------------------------------------------
1............................                5  February 19, 2003.
2, 6.........................                4  February 7, 2003.
3............................                3  November 5, 2001.
4, 5.........................                2  August 3, 2001.
------------------------------------------------------------------------

    Goodrich Service Bulletin 2-1530-32-2, Revision 5, contains the 
following effective pages:

------------------------------------------------------------------------
                                Revision level
         Page number            shown on page      Date  shown on page
------------------------------------------------------------------------
1............................                5  February 19, 2003.
2, 6.........................                4  February 7, 2003.
3............................                3  November 30, 2001.
4, 5.........................                2  August 3, 2001.
------------------------------------------------------------------------

    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 Cessna Aircraft Co., P.O. Box 
7706, Wichita, Kansas 67277. Copies may be inspected at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; at the FAA, Wichita Aircraft Certification Office, 1801 
Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or 
at the Office of the Federal Register, 800 North Capitol Street, 
NW., suite 700, Washington, DC.

Effective Date

    (i) This amendment becomes effective on June 2, 2004.

    Issued in Renton, Washington, on April 16, 2004.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-9380 Filed 4-27-04; 8:45 am]
BILLING CODE 4910-13-P