[Federal Register: June 15, 2004 (Volume 69, Number 114)]
[Rules and Regulations]
[Page 33285-33287]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr15jn04-4]
=======================================================================
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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
----------------------------------------------------------------------------------------------------------------
Service bulletin Revision Date
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------
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