[Federal Register Volume 69, Number 114 (Tuesday, June 15, 2004)]
[Rules and Regulations]
[Pages 33285-33287]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-13336]


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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; correction.

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SUMMARY: This document corrects information in an existing 
airworthiness directive (AD) that applies to certain Cessna Model 500, 
501, 550, and 551 airplanes. That AD currently 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. That AD also requires that the 
existing markings on the piston housing of certain brake assemblies be 
eliminated. This document corrects the compliance time for the 
inspection for cracked or broken stator disks on certain airplanes. 
This correction is necessary to ensure that affected airplanes are 
given sufficient time to comply with the requirements of this AD.

DATES: Effective June 2, 2004.
    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of June 2, 2004 (69 FR 23093, April 28, 2004).

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) 946-4107.

SUPPLEMENTARY INFORMATION: On April 16, 2004, the Federal Aviation 
Administration (FAA) issued AD 2004-09-05, amendment 39-13594 (69 FR 
23093, April 28, 2004), which applies to certain Cessna Model 500, 501, 
550, and 551 airplanes. That AD 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. That AD also requires that the existing markings on the 
piston housing of certain brake assemblies be eliminated. That AD was 
prompted by several reports of wheel lockups that appear to be caused 
by cracked or broken brake stator disks becoming jammed in the brake 
assembly and preventing rotation. The actions required by that AD are 
intended to prevent such wheel lockups and consequent jamming of the 
brake assembly, which may result in reduced directional control or 
braking performance during landing.

Need for the Correction

    We recently obtained information which indicates that the 
compliance time for the inspection for cracked or broken stator disks 
on airplanes that do not use thrust reversers was stated incorrectly. 
Paragraph (b)(2) of the AD specifies that this inspection must be 
accomplished prior to the accumulation of 200 total landings on the 
brake assembly, or within 25 landings after the effective date of the 
AD, whichever is later. However, the compliance time for determining 
whether the stator disks are subject to this inspection, as stated in 
paragraph (a) of the AD, is 50 landings or 90 days after the effective 
date of the AD, whichever is first. The disparity between the 
compliance times--50 landings after the effective date of the AD for 
the initial inspection versus 25 landings after the effective date of 
the AD for the follow-on inspection--could result in certain airplanes 
being out of compliance with the requirements of paragraph (b)(2) of 
the AD before that airplane reaches the initial compliance time in 
paragraph (a) of the AD. To ensure that affected operators are given 
sufficient time to comply with the requirements of this AD, the grace 
period in paragraph (b)(2) of the AD should have been 50 landings, 
rather than 25 landings, after the effective date of the AD.
    The FAA has determined that a correction to AD 2004-09-05 is 
necessary. The correction will revise the grace period portion of the 
compliance time in paragraph (b)(2) of the AD from 25 landings to 50 
landings after the effective date of the AD.

Correction of Publication

    This document corrects the error and correctly adds the AD as an 
amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 
39.13).
    The AD is reprinted in its entirety for the convenience of affected 
operators. The effective date of the AD remains June 2, 2004.
    Since this action only extends the compliance time specified in 
paragraph (b)(2) of the AD, it has no adverse economic impact and 
imposes no additional burden on any person. Therefore, the FAA has 
determined that

[[Page 33286]]

notice and public procedures are unnecessary.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Correction

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  [Corrected]

0
2. Section 39.13 is amended by correctly adding the following 
airworthiness directive (AD):

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 50 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.

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 2-1528-32-3..  Original...................  March 23, 2000.
BFGoodrich Service Bulletin 2-1530-32-3..  Original...................  March 23, 2000.

[[Page 33287]]

 
Goodrich Service Bulletin 2-1528-32-2....  5..........................  February 19, 2003.
Goodrich Service Bulletin 2-1530-32-2....  5..........................  February 19, 2003.
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    This incorporation by reference was approved previously by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51 as of June 2, 2004 (69 FR 23093, April 28, 2004). 
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 National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, call (202) 741-6030, or go 
to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

Effective Date

    (i) The effective date of this amendment remains June 2, 2004.

    Issued in Renton, Washington, on June 7, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-13336 Filed 6-14-04; 8:45 am]
BILLING CODE 4910-13-P