[Federal Register: April 28, 2004 (Volume 69, Number 82)]
[Rules and Regulations]
[Page 23093-23095]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr28ap04-3]
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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
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1............................ 5 February 19, 2003.
2, 6......................... 4 February 7, 2003.
3............................ 3 November 5, 2001.
4, 5......................... 2 August 3, 2001.
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Goodrich Service Bulletin 2-1530-32-2, Revision 5, contains the
following effective pages:
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Revision level
Page number shown on page Date shown on page
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1............................ 5 February 19, 2003.
2, 6......................... 4 February 7, 2003.
3............................ 3 November 30, 2001.
4, 5......................... 2 August 3, 2001.
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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]
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