FAA airworthiness directive publication

AD 2004-09-05

2004-06-15 · Correction notice · Federal Register document 04-13336

This page records a selected historical publication. Its current legal status, applicability to an individual aircraft and compliance have not been determined. Consult the current FAA directive and aircraft configuration and maintenance records.

This correction remains a separate publication; it is not presented as a newly issued independent directive.

What this historical correction says

Source publication 2004-06-15 · Document 04-13336.

The notice republishes the complete rule. The complete applicability clause from this reprint is retained below with its conditions unevaluated.

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.

Original date wording

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).

Dates describing the correction and the original rule remain separate as written.

Complete applicability clause in this reprint

    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.

Literal source labels for discovery: 500, 501, 550, 551. Labels remain as written; series, aliases and engine suffixes are not expanded.

Dated original publication

AD 2004-09-05 · 2004-04-28 · document 04-9380

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.

Each link opens a separate dated source. These words and dates do not determine which directive controls today, aircraft applicability, installed configuration or compliance. No corrected rule body has been merged.

Historical relationship observation unknown

This correction notice is a separate source edition and was not interpreted as a new rule. This does not establish that there are no related or currently applicable directives.

Earlier extraction record

The earlier extraction kept these fields unknown. Its original record is preserved below. Newly retained correction excerpts are shown above; applicability and compliance remain undetermined.

Applicability text in this publication

An applicability clause was not extracted from this publication. Applicability remains undetermined.

Effective-date text

An effective-date observation was not extracted from this publication.

Publication context

A relationship to prior directives has not been established from this publication.

Official sources

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This selected source edition is not a complete list of current airworthiness directives. Referenced manufacturer service documents are not reproduced here.