Airworthiness Directives; McDonnell Douglas Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 Airplanes; Model DC-8F-54 and DC-8F-55 Airplanes; Model DC-8-50, -60, -60F, -70, and -70F Series Airplanes; Model DC-9-10, -20, -30, -40, and -50 Series Airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) Airplanes; and Model MD-88 Airplanes, 18201-18205 [06-3380]
Download as PDF
<![CDATA[
Federal Register / Vol. 71, No. 69 / Tuesday, April 11, 2006 / Rules and Regulations
HCM30033N has also been installed: Modify
the control cable duct on the left bulkhead
structure at frame 12 and the forward toilet
bulkhead structure in accordance with Parts
1 and 2 of the Accomplishment Instructions
of the service bulletin.
Modifications Accomplished According to
Previous Issue of Service Bulletin
(g) Modifications accomplished before the
effective date of this AD in accordance with
BAE Systems (Operations) Limited
Modification Service Bulletin SB.25–459–
36241A, dated July 22, 2004, are considered
acceptable for compliance with the
corresponding action specified in this AD.
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Related Information
(i) British airworthiness directive G–2005–
0026, dated September 21, 2005, also
addresses the subject of this AD.
Material Incorporated by Reference
wwhite on PROD1PC61 with NOTICES
(j) You must use BAE Systems (Operations)
Limited Modification Service Bulletin SB.25–
459–36241A, Revision 1, dated March 30,
2005, to perform the actions that are required
by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact British Aerospace Regional Aircraft
American Support, 13850 Mclearen Road,
Herndon, Virginia 20171, for a copy of this
service information. You may review copies
at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street SW., Room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on March
30, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–3379 Filed 4–10–06; 8:45 am]
BILLING CODE 4910–13–P
VerDate Aug<31>2005
15:47 Apr 10, 2006
Jkt 208001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20797; Directorate
Identifier 2004–NM–256–AD; Amendment
39–14552; AD 2006–07–25]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model DC–8–11, DC–8–12,
DC–8–21, DC–8–31, DC–8–32, DC–8–
33, DC–8–41, DC–8–42, and DC–8–43
Airplanes; Model DC–8F–54 and DC–
8F–55 Airplanes; Model DC–8–50, –60,
–60F, –70, and –70F Series Airplanes;
Model DC–9–10, –20, –30, –40, and –50
Series Airplanes; Model DC–9–81 (MD–
81), DC–9–82 (MD–82), DC–9–83 (MD–
83), and DC–9–87 (MD–87) Airplanes;
and Model MD–88 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain McDonnell
Douglas airplanes, as listed above. That
AD currently requires an initial general
visual or dye penetrant inspection,
repetitive dye penetrant inspections,
and replacement, as necessary, of the
rudder pedal bracket. This new AD also
requires, for certain airplanes, replacing
the rudder pedal bracket assemblies
with new, improved parts, which
terminates the repetitive inspections.
This AD results from a report of
numerous cracked rudder pedal
brackets found during inspections of
certain affected airplanes. We are
issuing this AD to prevent failure of the
rudder pedal bracket assembly, which
could result in the loss of rudder and
braking control at either the captain’s or
first officer’s position.
DATES: This AD becomes effective May
16, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of May 16, 2006.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., Nassif Building, room PL–401,
Washington, DC.
Contact Boeing Commercial
Airplanes, Long Beach Division, 3855
Lakewood Boulevard, Long Beach,
California 90846, Attention: Data and
Service Management, Dept. C1–L5A
SUMMARY:
PO 00000
Frm 00041
Fmt 4700
Sfmt 4700
18201
(D800–0024), for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Wahib Mina, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office,
3960 Paramount Boulevard, Lakewood,
California 90712–4137; telephone (562)
627–5324; fax (562) 627–5210.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 89–14–02, amendment
39–6245 (54 FR 27156, June 28, 1989).
The existing AD applies to certain
McDonnell Douglas Model DC–8–11,
DC–8–12, DC–8–21, DC–8–31, DC–8–32,
DC–8–33, DC–8–41, DC–8–42, and DC–
8–43 airplanes; Model DC–8F–54 and
DC–8F–55 airplanes; and Model DC–8–
50, –60, –60F, –70, and –70F series
airplanes (hereafter referred to as DC–8
airplanes). The existing AD also applies
to McDonnell Douglas Model DC–9–10,
–20, –30, –40, and –50 series airplanes;
Model DC–9–81 (MD–81), DC–9–82
(MD–82), DC–9–83 (MD–83), and DC–9–
87 (MD–87) airplanes; and Model MD–
88 airplanes (hereafter referred to as
DC–9/MD–80 airplanes). That NPRM
was published in the Federal Register
on April 5, 2005 (70 FR 17216). That
NPRM proposed to continue to require
an initial general visual or dye penetrant
inspection, repetitive dye penetrant
inspections, and replacement, as
necessary, of the rudder pedal bracket.
That NPRM also proposed to require, for
certain airplanes, replacing the rudder
pedal bracket assemblies with new,
improved parts, which would terminate
the repetitive inspections.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been received on the NPRM.
E:\FR\FM\11APR1.SGM
11APR1
18202
Federal Register / Vol. 71, No. 69 / Tuesday, April 11, 2006 / Rules and Regulations
Request To Reference Previous Service
Bulletins
Boeing requests that we reference
Revisions 4, 5, and 6 of McDonnell
Douglas DC–9 Alert Service Bulletin
A27–307 for accomplishing the actions
in this AD. Revisions 4, 5, and 6 of the
service bulletin were approved
previously as alternative methods of
compliance (AMOCs) for paragraphs A
and B of AD 89–14–02, which
correspond to paragraphs (f) and (g) of
this AD. Therefore, we infer the
commenter would like us to add
references to Revisions 4 and 5 of the
service bulletin to paragraph (h) of this
AD.
We agree to reference Revision 4,
dated June 3, 1991, and Revision 5,
dated February 14, 1992, of McDonnell
Douglas DC–9 Alert Service Bulletin
A27–307 in paragraph (h) of this AD,
since the procedures in those revisions
are essentially the same as those in
Revision 6. As a result, we have not
retained paragraph (i) of the NPRM,
Credit for Previous Service Bulletins, in
this AD.
Request To Revise the Cost of
Compliance
Alaska Airlines requests that we
increase the estimated cost of parts to
$9,882. The commenter states that the
captain’s rudder pedal bracket assembly
(part number (P/N) 5962903–501) costs
$4,769, and that the first officer’s rudder
pedal bracket assembly (P/N 5962904–
501) costs $5,113. The commenter also
states that these are the current prices
quoted by the manufacturer, and that
the prices may be considerably higher
when an airplane has accumulated
75,000 total flight cycles (the
compliance time for the replacements).
We agree. We have confirmed with
Boeing that since issuance of McDonnell
Douglas DC–9 Alert Service Bulletin
A27–307, Revision 6, dated December
19, 1994, the cost of the parts has
increased as quoted by the commenter.
Therefore, we have revised the
Estimated Costs table in this AD
accordingly.
wwhite on PROD1PC61 with NOTICES
Request To Terminate AD 89–14–02
Boeing also requests that we terminate
AD 89–14–02 instead of supersede it.
Boeing proposes that we revise
paragraph (b) of the NPRM to state that
first accomplishment of paragraphs
(f)(1) and (f)(2) constitutes terminating
action for the repetitive inspections of
AD 89–14–02. As justification, Boeing
asserts that this change will make it
easier for operators to track compliance.
We do not agree to revise paragraph
(b) of this AD. Since this AD supersedes
VerDate Aug<31>2005
15:47 Apr 10, 2006
Jkt 208001
AD 89–14–02, the requirements of this
AD replace the requirements of that
existing AD. After the effective date of
this AD, operators would be required to
show compliance with this AD, not AD
89–14–02. Furthermore, we have carried
over the repetitive inspections and
compliance times from AD 89–14–02
into this AD because those inspections
continue to be required until the
terminating action in this AD is
accomplished for certain airplanes. To
revise this AD as the commenter
proposes would necessitate revising the
compliance times in paragraphs (f) and
(g) of this AD to account for operators
who are currently inspecting in
accordance with AD 89–14–02.
Therefore, no change to this AD is
necessary in this regard.
Request To Address Defective Parts
Manufacturer Approval (PMA) Parts
The Modification and Repair Parts
Association (MARPA) requests we
revise the NPRM to cover possible
defective PMA alternative parts, rather
than just the parts identified in the
NPRM, so that those defective PMA
parts also are subject to the NPRM.
MARPA states that there are existing
PMA parts for the rudder pedal
brackets. MARPA also states that PMA
manufacturers are encouraged—and in
some cases, required—to identify PMA
parts by alternative designations.
We concur with the MARPA’s general
request that, if we know that an unsafe
condition also exists in PMA parts, the
AD should address those parts, as well
as the original parts. However, we are
not aware of other PMA parts that are
equivalent to the defective rudder pedal
bracket assemblies. In the event PMA
equivalent parts are identified, we will
consider further rulemaking.
The MARPA’s remarks are timely in
that the Transport Airplane Directorate
currently is in the process of reviewing
this issue as it applies to transport
category airplanes. We acknowledge
that there may be other ways of
addressing this issue to ensure that
unsafe PMA parts are identified and
addressed. Once we have thoroughly
examined all aspects of this issue,
including input from industry, and have
made a final determination, we will
consider whether our policy regarding
addressing PMA parts in ADs needs to
be revised. We consider that to delay
this AD action would be inappropriate,
since we have determined that an
unsafe condition exists and that
replacement of certain parts must be
accomplished to ensure continued
safety. Therefore, no change has been
made to this AD in this regard.
PO 00000
Frm 00042
Fmt 4700
Sfmt 4700
Request To Reference PMA Parts
MARPA also requests that we revise
language in the NPRM to permit
installation of PMA equivalent parts.
MARPA states that the mandated
installation of a certain part number ‘‘is
at variance with FAR 21.303,’’ which
permits the installation of other (PMA)
parts.
We infer that the commenter would
like this AD to permit installation of any
equivalent PMA parts so that it is not
necessary for an operator to request
approval of an alternative method of
compliance (AMOC) in order to install
an ‘‘equivalent’’ PMA part. Whether an
alternative part is ‘‘equivalent’’ in
adequately resolving the unsafe
condition can only be determined on a
case-by-case basis, based on a complete
understanding of the unsafe condition.
We are not currently aware of any such
parts. Our policy is that, in order for
operators to replace a part with one that
is not specified in the AD, they must
request an AMOC. This is necessary so
that we can make a specific
determination that an alternative part is
or is not susceptible to the same unsafe
condition.
In response to the MARPA’s statement
regarding a ‘‘variance with FAR
21.303,’’ under which the FAA issues
PMAs, this statement appears to reflect
a misunderstanding of the relationship
between ADs and the certification
procedural regulations of part 21 of the
Federal Aviation Regulations (14 CFR
part 21). Those regulations, including
section 21.303 of the Federal Aviation
Regulations (14 CFR 21.303), are
intended to ensure that aeronautical
products comply with the applicable
airworthiness standards. But ADs are
issued when, notwithstanding those
procedures, we become aware of unsafe
conditions in these products or parts.
Therefore, an AD takes precedence over
other design approvals when we
identify an unsafe condition, and
mandating installation of a certain part
number in an AD is not at variance with
section 21.303.
The AD provides a means of
compliance for operators to ensure that
the identified unsafe condition is
addressed appropriately. For an unsafe
condition attributable to a part, the AD
normally identifies the replacement
parts necessary to obtain that
compliance. As stated in section 39.7 of
the Federal Aviation Regulations (14
CFR 39.7): ‘‘Anyone who operates a
product that does not meet the
requirements of an applicable
airworthiness directive is in violation of
this section.’’ Unless an operator obtains
approval for an AMOC, replacing a part
E:\FR\FM\11APR1.SGM
11APR1
18203
Federal Register / Vol. 71, No. 69 / Tuesday, April 11, 2006 / Rules and Regulations
with one not specified by the AD would
make the operator subject to an
enforcement action and result in a civil
penalty. No change to this AD is
necessary in this regard.
Change To Certain Service Bulletin
References
We referenced McDonnell Douglas
DC–8 Alert Service Bulletin A27–273
and McDonnell Douglas DC–9 Alert
Service Bulletin A27–307, both dated
May 16, 1989, as applicable, as the
appropriate source of service
information for accomplishing the
actions required by AD 89–14–02.
However, we inadvertently omitted the
revision level of those service bulletins
in AD 89–14–02. We have corrected
those references in paragraph (f) and
Note 2 of this AD.
Clarification of AMOC Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been received, and determined
that air safety and the public interest
require adopting the AD with the
changes described previously. We have
determined that these changes will
neither increase significantly the burden
on any operator nor increase the scope
of the AD.
Costs of Compliance
There are about 2,025 airplanes of the
affected design in the worldwide fleet.
This AD affects about 1,381 airplanes of
U.S. registry; about 250 of those
airplanes are Model DC–8 airplanes and
about 1,131 are Model DC–9/MD–80
airplanes. The new replacements of this
AD are applicable only to Model DC–9/
MD–80 airplanes. The following table
provides the estimated costs for U.S.
operators to comply with this AD.
ESTIMATED COSTS
Work
hours
Average
labor
rate per
hour
General visual inspection (required by AD 89–14–02) ....................
Dye penetrant inspection (required by AD 89–14–02) .....................
3
5
$65
65
None
None
Replacements (new action) ..............................................................
9
65
$9,882
Action
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
wwhite on PROD1PC61 with NOTICES
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
VerDate Aug<31>2005
15:47 Apr 10, 2006
Jkt 208001
Cost per
airplane
Parts
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
Number of
U.S.-registered airplanes
$195
$325, per inspection
cycle
$10,467
1,381
1,381
1,131
Fleet cost
$269,295
$448,825, per
inspection
cycle
$11,838,177
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–6245 (54
FR 27156, June 28, 1989) and by adding
the following new airworthiness
directive (AD):
I
2006–07–25 McDonnell Douglas:
Amendment 39–14552. Docket No.
FAA–2005–20797; Directorate Identifier
2004–NM–256–AD.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Effective Date
(a) This AD becomes effective May 16,
2006.
Affected ADs
(b) This AD supersedes AD 89–14–02.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
I
PO 00000
Frm 00043
Fmt 4700
Sfmt 4700
Applicability
(c) This AD applies to the airplanes listed
in Table 1 of this AD, certificated in any
category.
E:\FR\FM\11APR1.SGM
11APR1
18204
Federal Register / Vol. 71, No. 69 / Tuesday, April 11, 2006 / Rules and Regulations
TABLE 1.—APPLICABILITY
McDonnell Douglas
As identified in-
Model DC–8–11, DC–8–12, DC–8–21, DC–8–31, DC–8–32, DC–8–33, DC–8–41, DC–8–42, and DC–8–43 airplanes; Model DC–8–51, DC–8–52, DC–8–53, and DC–8–55 airplanes; Model DC–8F–54 and DC–8F–55 airplanes; Model DC–8–61, DC–8–62, and DC–8–63 airplanes; Model DC–8–61F, DC–8–62F, and DC–8–63F airplanes; Model DC–8–71, DC–8–72, and DC–8–73 airplanes.
Model DC–9–11, DC–9–12, DC–9–13, DC–9–14, DC–9–15, and DC–9–15F airplanes; Model DC–9–21 airplanes;
Model DC–9–31, DC–9–32, DC–9–32 (VC–9C), DC–9–32F, DC–9–33F, DC–9–34, DC–9–34F, and DC–9–32F
(C–9A, C–9B) airplanes; Model DC–9–41 airplanes; Model DC–9–51 airplanes; DC–9–81 (MD–81), DC–9–82
(MD–82), DC–9–83 (MD–83), and DC–9–87 (MD–87) airplanes; and Model MD–88 airplanes.
McDonnell Douglas DC–8
Alert Service Bulletin
A27–273, dated May 16,
1989.
McDonnell Douglas DC–9
Alert Service Bulletin
Model A27–307, Revision
6, dated December 19,
1994.
Unsafe Condition
(d) This AD was prompted by a report of
numerous cracked rudder pedal brackets
found during inspections of certain affected
airplanes. We are issuing this AD to prevent
failure of the rudder pedal bracket assembly,
which could result in the loss of rudder and
braking control at either the captain’s or first
officer’s position.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
wwhite on PROD1PC61 with NOTICES
Requirements of AD 89–14–02
(f) Prior to the accumulation of 40,000 total
landings or within 30 days after July 5, 1989
(the effective date of AD 89–14–02),
whichever occurs later, perform either a
general visual inspection or dye penetrant
inspection for cracks of the captain’s and first
officer’s rudder pedal bracket, part numbers
(P/N) 5616067 and 5616068, respectively, in
accordance with McDonnell Douglas DC–8
Alert Service Bulletin A27–273 (for Model
DC–8–11, DC–8–12, DC–8–21, DC–8–31, DC–
8–32, DC–8–33, DC–8–41, DC–8–42, and DC–
8–43 airplanes; Model DC–8–51, DC–8–52,
DC–8–53, and DC–8–55 airplanes; Model
DC–8F–54 and DC–8F–55 airplanes; Model
DC–8–61, DC–8–62, and DC–8–63 airplanes;
Model DC–8–61F, DC–8–62F, and DC–8–63F
airplanes; Model DC–8–71, DC–8–72, and
DC–8–73 airplanes), or McDonnell Douglas
DC–9 Alert Service Bulletin A27–307 (for
Model DC–9–11, DC–9–12, DC–9–13, DC–9–
14, DC–9–15, and DC–9–15F airplanes;
Model DC–9–21 airplanes; Model DC–9–31,
DC–9–32, DC–9–32 (VC–9C), DC–9–32F, DC–
9–33F, DC–9–34, DC–9–34F, and DC–9–32F
(C–9A, C–9B) airplanes; Model DC–9–41
airplanes; Model DC–9–51 airplanes; Model
DC–9–81 (MD–81), DC–9–82 (MD–82), DC–
9–83 (MD–83), and DC–9–87 (MD–87)
airplanes; and Model MD–88 airplanes), both
Revision 1, both dated May 16, 1989, as
applicable.
Note 1: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
examination of an interior or exterior area,
installation, or assembly to detect obvious
damage, failure, or irregularity. This level of
inspection is made from within touching
distance unless otherwise specified. A mirror
may be necessary to ensure visual access to
all surfaces in the inspection area. This level
of inspection is made under normally
available lighting conditions such as
daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
Note 2: McDonnell Douglas DC–8 Alert
Service Bulletin A27–273 and McDonnell
Douglas DC–9 Alert Service Bulletin A27–
307, both Revision 1, both dated May 16,
1989, are hereinafter referred to as ASB A27–
273 and ASB A27–307, respectively.
(1) If an initial general visual inspection is
accomplished, and no cracks are found,
perform a dye penetrant inspection of the
rudder pedal bracket assembly within 180
days after the general visual inspection, and
thereafter accomplish dye penetrant
inspections at intervals not to exceed 12
months or 2,500 landings, whichever occurs
earlier.
(2) If an initial dye penetrant inspection is
accomplished, and no cracks are found,
accomplish repetitive dye penetrant
inspections at intervals not to exceed 12
months or 2,500 landings, whichever occurs
earlier.
(g) If cracks are detected, prior to further
flight, remove and replace the rudder pedal
bracket assembly in accordance with ASB
A27–273 or A27–307, as applicable. Prior to
the accumulation of 40,000 total landings
after replacement with the new part, resume
the repetitive inspections in accordance with
paragraph (f) in this AD.
New Requirements of This AD
Terminating Action for Certain Airplanes
(h) For McDonnell Douglas Model DC–9–
11, DC–9–12, DC–9–13, DC–9–14, DC–9–15,
and DC–9–15F airplanes; Model DC–9–21
airplanes; Model DC–9–31, DC–9–32, DC–9–
32 (VC–9C), DC–9–32F, DC–9–33F, DC–9–34,
DC–9–34F, and DC–9–32F (C–9A, C–9B)
airplanes; Model DC–9–41 airplanes; Model
DC–9–51 airplanes; Model DC–9–81 (MD–
81), DC–9–82 (MD–82), DC–9–83 (MD–83),
DC–9–87 (MD–87) airplanes; and Model MD–
88 airplanes: Do the actions in paragraphs
(h)(1) and (h)(2) of this AD in accordance
with the Accomplishment Instructions of
McDonnell Douglas DC–9 Alert Service
Bulletin A27–307, Revision 4, dated June 3,
1991; Revision 5, dated February 14, 1992; or
Revision 6, dated December 19, 1994.
(1) Before the accumulation of 75,000 total
landings on the captain’s rudder pedal
bracket assembly, P/N 5616067–501, or
within 60 months after the effective date of
this AD, whichever occurs later: Remove the
rudder pedal bracket assembly and replace it
with new, improved P/N 5962903–501.
Accomplishment of the replacement
terminates the repetitive inspections of the
captain’s rudder pedal bracket assembly
required by paragraphs (f) and (g) of this AD.
(2) Before the accumulation of 75,000 total
landings on the first officer’s rudder pedal
bracket assembly, P/N 5616068–501, or
within 60 months after the effective date of
this AD, whichever occurs later: Remove the
rudder pedal bracket assembly and replace it
with new, improved P/N 5962904–501.
Accomplishment of the replacement
terminates the repetitive inspections of the
first officer’s rudder pedal bracket assembly
required by paragraphs (f) and (g) of this AD.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, Los Angeles Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
(3) AMOCs, approved previously in
accordance with AD 89–14–02, amendment
39–6245, are approved as AMOCs for the
corresponding requirements of this AD.
Material Incorporated by Reference
(j) You must use the applicable service
information identified in Table 2 of this AD
to perform the actions that are required by
this AD, unless the AD specifies otherwise.
TABLE 2.—MATERIAL INCORPORATED BY REFERENCE
Service bulletin
Revision level
McDonnell Douglas DC–8 Alert Service Bulletin A27–273 ..................................................................
VerDate Aug<31>2005
15:47 Apr 10, 2006
Jkt 208001
PO 00000
Frm 00044
Fmt 4700
Sfmt 4700
E:\FR\FM\11APR1.SGM
1
11APR1
Date
May 16, 1989.
18205
Federal Register / Vol. 71, No. 69 / Tuesday, April 11, 2006 / Rules and Regulations
TABLE 2.—MATERIAL INCORPORATED BY REFERENCE—Continued
Service bulletin
McDonnell
McDonnell
McDonnell
McDonnell
Douglas
Douglas
Douglas
Douglas
DC–9
DC–9
DC–9
DC–9
Alert
Alert
Alert
Alert
Service
Service
Service
Service
Bulletin
Bulletin
Bulletin
Bulletin
A27–307
A27–307
A27–307
A27–307
Revision level
..................................................................
..................................................................
..................................................................
..................................................................
1
4
5
6
Date
May 16, 1989.
June 3, 1991.
February 14, 1992.
December 19, 1994.
McDonnell Douglas Alert Service Bulletin
A27–307, Revision 6, dated December 19,
1994, contains the following effective pages:
Revision level
shown on page
Page Number
1–24 ......................................................................................................................................................
25–36 ....................................................................................................................................................
The Director of the Federal Register
approved the incorporation by reference of
these documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Contact Boeing
Commercial Airplanes, Long Beach Division,
3855 Lakewood Boulevard, Long Beach,
California 90846, Attention: Data and Service
Management, Dept. C1–L5A (D800–0024), for
a copy of this service information. You may
review copies at the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street SW., room PL–401, Nassif
Building, Washington, DC; on the Internet at
https://dms.dot.gov; or at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at the NARA, call (202) 741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on March
31, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–3380 Filed 4–10–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23816; Directorate
Identifier 2005–NM–247–AD; Amendment
39–14553; AD 2006–07–26]
RIN 2120–AA64
Airworthiness Directives; Aerospatiale
Model ATR42 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
wwhite on PROD1PC61 with NOTICES
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
VerDate Aug<31>2005
15:47 Apr 10, 2006
Jkt 208001
Aerospatiale Model ATR42 airplanes.
This AD requires one-time inspections
to detect discrepancies (e.g., cracking,
loose/sheared fasteners, distortion) of
the upper skin and rib feet of the outer
wing boxes, and repair if necessary.
This AD results from a report of
cracking on the upper skin and ribs of
the outer wing box on an in-service
airplane. We are issuing this AD to
detect and correct these discrepancies,
which could result in reduced structural
integrity of the airplane.
DATES: This AD becomes effective May
16, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of May 16, 2006.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Aerospatiale, 316 Route de
Bayonne, 31060 Toulouse, Cedex 03,
France, for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 227–1137; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
PO 00000
Frm 00045
Fmt 4700
Sfmt 4700
6
5
Date shown on page
December 19, 1994.
February 14, 1992.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to all Aerospatiale Model ATR42
airplanes. That NPRM was published in
the Federal Register on February 8,
2006 (71 FR 6413). That NPRM
proposed to require one-time
inspections to detect discrepancies (e.g.,
cracking, loose/sheared fasteners,
distortion) of the upper skin and rib feet
of the outer wing boxes, and repair if
necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We received no
comments on the NPRM or on the
determination of the cost to the public.
Clarification of Reporting
In the preamble of the NPRM we
stated that although ‘‘the French
airworthiness directive and the service
bulletin specify to submit certain
information to the manufacturer, this
proposed AD does not include that
requirement.’’ However, we did not
include this exception in the body of the
NPRM. We have added paragraph (h) to
clarify that reporting is not required.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD with the change
described previously. We have
determined that this change will neither
E:\FR\FM\11APR1.SGM
11APR1
]]>Agencies
[Federal Register Volume 71, Number 69 (Tuesday, April 11, 2006)]
[Rules and Regulations]
[Pages 18201-18205]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-3380]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20797; Directorate Identifier 2004-NM-256-AD;
Amendment 39-14552; AD 2006-07-25]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-8-11, DC-8-
12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43
Airplanes; Model DC-8F-54 and DC-8F-55 Airplanes; Model DC-8-50, -60, -
60F, -70, and -70F Series Airplanes; Model DC-9-10, -20, -30, -40, and
-50 Series Airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83
(MD-83), and DC-9-87 (MD-87) Airplanes; and Model MD-88 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain McDonnell Douglas airplanes, as listed
above. That AD currently requires an initial general visual or dye
penetrant inspection, repetitive dye penetrant inspections, and
replacement, as necessary, of the rudder pedal bracket. This new AD
also requires, for certain airplanes, replacing the rudder pedal
bracket assemblies with new, improved parts, which terminates the
repetitive inspections. This AD results from a report of numerous
cracked rudder pedal brackets found during inspections of certain
affected airplanes. We are issuing this AD to prevent failure of the
rudder pedal bracket assembly, which could result in the loss of rudder
and braking control at either the captain's or first officer's
position.
DATES: This AD becomes effective May 16, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of May 16, 2006.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., Nassif Building,
room PL-401, Washington, DC.
Contact Boeing Commercial Airplanes, Long Beach Division, 3855
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and
Service Management, Dept. C1-L5A (D800-0024), for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT: Wahib Mina, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone (562) 627-5324; fax (562) 627-5210.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at https://dms.dot.gov or in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 89-14-02, amendment 39-
6245 (54 FR 27156, June 28, 1989). The existing AD applies to certain
McDonnell Douglas Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32,
DC-8-33, DC-8-41, DC-8-42, and DC-8-43 airplanes; Model DC-8F-54 and
DC-8F-55 airplanes; and Model DC-8-50, -60, -60F, -70, and -70F series
airplanes (hereafter referred to as DC-8 airplanes). The existing AD
also applies to McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50
series airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-
83), and DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes
(hereafter referred to as DC-9/MD-80 airplanes). That NPRM was
published in the Federal Register on April 5, 2005 (70 FR 17216). That
NPRM proposed to continue to require an initial general visual or dye
penetrant inspection, repetitive dye penetrant inspections, and
replacement, as necessary, of the rudder pedal bracket. That NPRM also
proposed to require, for certain airplanes, replacing the rudder pedal
bracket assemblies with new, improved parts, which would terminate the
repetitive inspections.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.
[[Page 18202]]
Request To Reference Previous Service Bulletins
Boeing requests that we reference Revisions 4, 5, and 6 of
McDonnell Douglas DC-9 Alert Service Bulletin A27-307 for accomplishing
the actions in this AD. Revisions 4, 5, and 6 of the service bulletin
were approved previously as alternative methods of compliance (AMOCs)
for paragraphs A and B of AD 89-14-02, which correspond to paragraphs
(f) and (g) of this AD. Therefore, we infer the commenter would like us
to add references to Revisions 4 and 5 of the service bulletin to
paragraph (h) of this AD.
We agree to reference Revision 4, dated June 3, 1991, and Revision
5, dated February 14, 1992, of McDonnell Douglas DC-9 Alert Service
Bulletin A27-307 in paragraph (h) of this AD, since the procedures in
those revisions are essentially the same as those in Revision 6. As a
result, we have not retained paragraph (i) of the NPRM, Credit for
Previous Service Bulletins, in this AD.
Request To Revise the Cost of Compliance
Alaska Airlines requests that we increase the estimated cost of
parts to $9,882. The commenter states that the captain's rudder pedal
bracket assembly (part number (P/N) 5962903-501) costs $4,769, and that
the first officer's rudder pedal bracket assembly (P/N 5962904-501)
costs $5,113. The commenter also states that these are the current
prices quoted by the manufacturer, and that the prices may be
considerably higher when an airplane has accumulated 75,000 total
flight cycles (the compliance time for the replacements).
We agree. We have confirmed with Boeing that since issuance of
McDonnell Douglas DC-9 Alert Service Bulletin A27-307, Revision 6,
dated December 19, 1994, the cost of the parts has increased as quoted
by the commenter. Therefore, we have revised the Estimated Costs table
in this AD accordingly.
Request To Terminate AD 89-14-02
Boeing also requests that we terminate AD 89-14-02 instead of
supersede it. Boeing proposes that we revise paragraph (b) of the NPRM
to state that first accomplishment of paragraphs (f)(1) and (f)(2)
constitutes terminating action for the repetitive inspections of AD 89-
14-02. As justification, Boeing asserts that this change will make it
easier for operators to track compliance.
We do not agree to revise paragraph (b) of this AD. Since this AD
supersedes AD 89-14-02, the requirements of this AD replace the
requirements of that existing AD. After the effective date of this AD,
operators would be required to show compliance with this AD, not AD 89-
14-02. Furthermore, we have carried over the repetitive inspections and
compliance times from AD 89-14-02 into this AD because those
inspections continue to be required until the terminating action in
this AD is accomplished for certain airplanes. To revise this AD as the
commenter proposes would necessitate revising the compliance times in
paragraphs (f) and (g) of this AD to account for operators who are
currently inspecting in accordance with AD 89-14-02. Therefore, no
change to this AD is necessary in this regard.
Request To Address Defective Parts Manufacturer Approval (PMA) Parts
The Modification and Repair Parts Association (MARPA) requests we
revise the NPRM to cover possible defective PMA alternative parts,
rather than just the parts identified in the NPRM, so that those
defective PMA parts also are subject to the NPRM. MARPA states that
there are existing PMA parts for the rudder pedal brackets. MARPA also
states that PMA manufacturers are encouraged--and in some cases,
required--to identify PMA parts by alternative designations.
We concur with the MARPA's general request that, if we know that an
unsafe condition also exists in PMA parts, the AD should address those
parts, as well as the original parts. However, we are not aware of
other PMA parts that are equivalent to the defective rudder pedal
bracket assemblies. In the event PMA equivalent parts are identified,
we will consider further rulemaking.
The MARPA's remarks are timely in that the Transport Airplane
Directorate currently is in the process of reviewing this issue as it
applies to transport category airplanes. We acknowledge that there may
be other ways of addressing this issue to ensure that unsafe PMA parts
are identified and addressed. Once we have thoroughly examined all
aspects of this issue, including input from industry, and have made a
final determination, we will consider whether our policy regarding
addressing PMA parts in ADs needs to be revised. We consider that to
delay this AD action would be inappropriate, since we have determined
that an unsafe condition exists and that replacement of certain parts
must be accomplished to ensure continued safety. Therefore, no change
has been made to this AD in this regard.
Request To Reference PMA Parts
MARPA also requests that we revise language in the NPRM to permit
installation of PMA equivalent parts. MARPA states that the mandated
installation of a certain part number ``is at variance with FAR
21.303,'' which permits the installation of other (PMA) parts.
We infer that the commenter would like this AD to permit
installation of any equivalent PMA parts so that it is not necessary
for an operator to request approval of an alternative method of
compliance (AMOC) in order to install an ``equivalent'' PMA part.
Whether an alternative part is ``equivalent'' in adequately resolving
the unsafe condition can only be determined on a case-by-case basis,
based on a complete understanding of the unsafe condition. We are not
currently aware of any such parts. Our policy is that, in order for
operators to replace a part with one that is not specified in the AD,
they must request an AMOC. This is necessary so that we can make a
specific determination that an alternative part is or is not
susceptible to the same unsafe condition.
In response to the MARPA's statement regarding a ``variance with
FAR 21.303,'' under which the FAA issues PMAs, this statement appears
to reflect a misunderstanding of the relationship between ADs and the
certification procedural regulations of part 21 of the Federal Aviation
Regulations (14 CFR part 21). Those regulations, including section
21.303 of the Federal Aviation Regulations (14 CFR 21.303), are
intended to ensure that aeronautical products comply with the
applicable airworthiness standards. But ADs are issued when,
notwithstanding those procedures, we become aware of unsafe conditions
in these products or parts. Therefore, an AD takes precedence over
other design approvals when we identify an unsafe condition, and
mandating installation of a certain part number in an AD is not at
variance with section 21.303.
The AD provides a means of compliance for operators to ensure that
the identified unsafe condition is addressed appropriately. For an
unsafe condition attributable to a part, the AD normally identifies the
replacement parts necessary to obtain that compliance. As stated in
section 39.7 of the Federal Aviation Regulations (14 CFR 39.7):
``Anyone who operates a product that does not meet the requirements of
an applicable airworthiness directive is in violation of this
section.'' Unless an operator obtains approval for an AMOC, replacing a
part
[[Page 18203]]
with one not specified by the AD would make the operator subject to an
enforcement action and result in a civil penalty. No change to this AD
is necessary in this regard.
Change To Certain Service Bulletin References
We referenced McDonnell Douglas DC-8 Alert Service Bulletin A27-273
and McDonnell Douglas DC-9 Alert Service Bulletin A27-307, both dated
May 16, 1989, as applicable, as the appropriate source of service
information for accomplishing the actions required by AD 89-14-02.
However, we inadvertently omitted the revision level of those service
bulletins in AD 89-14-02. We have corrected those references in
paragraph (f) and Note 2 of this AD.
Clarification of AMOC Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Conclusion
We have carefully reviewed the available data, including the
comments that have been received, and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We have determined that these changes will neither increase
significantly the burden on any operator nor increase the scope of the
AD.
Costs of Compliance
There are about 2,025 airplanes of the affected design in the
worldwide fleet. This AD affects about 1,381 airplanes of U.S.
registry; about 250 of those airplanes are Model DC-8 airplanes and
about 1,131 are Model DC-9/MD-80 airplanes. The new replacements of
this AD are applicable only to Model DC-9/MD-80 airplanes. The
following table provides the estimated costs for U.S. operators to
comply with this AD.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Average Number of
Work labor U.S.-
Action hours rate per Parts Cost per airplane registered Fleet cost
hour airplanes
----------------------------------------------------------------------------------------------------------------
General visual inspection 3 $65 None $195 1,381 $269,295
(required by AD 89-14-02).
Dye penetrant inspection 5 65 None $325, per 1,381 $448,825, per
(required by AD 89-14-02). inspection cycle inspection cycle
Replacements (new action)...... 9 65 $9,882 $10,467 1,131 $11,838,177
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD 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.
For the reasons discussed above, I certify that this AD:
(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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-6245 (54 FR 27156, June 28, 1989) and by adding
the following new airworthiness directive (AD):
2006-07-25 McDonnell Douglas: Amendment 39-14552. Docket No. FAA-
2005-20797; Directorate Identifier 2004-NM-256-AD.
Effective Date
(a) This AD becomes effective May 16, 2006.
Affected ADs
(b) This AD supersedes AD 89-14-02.
Applicability
(c) This AD applies to the airplanes listed in Table 1 of this
AD, certificated in any category.
[[Page 18204]]
Table 1.--Applicability
----------------------------------------------------------------------------------------------------------------
McDonnell Douglas As identified in-
----------------------------------------------------------------------------------------------------------------
Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, McDonnell Douglas DC-8 Alert Service Bulletin A27-
DC-8-41, DC-8-42, and DC-8-43 airplanes; Model DC-8-51, DC- 273, dated May 16, 1989.
8-52, DC-8-53, and DC-8-55 airplanes; Model DC-8F-54 and
DC-8F-55 airplanes; Model DC-8-61, DC-8-62, and DC-8-63
airplanes; Model DC-8-61F, DC-8-62F, and DC-8-63F
airplanes; Model DC-8-71, DC-8-72, and DC-8-73 airplanes.
Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, and DC-9- McDonnell Douglas DC-9 Alert Service Bulletin Model
15F airplanes; Model DC-9-21 airplanes; Model DC-9-31, DC- A27-307, Revision 6, dated December 19, 1994.
9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-
34F, and DC-9-32F (C-9A, C-9B) airplanes; Model DC-9-41
airplanes; Model DC-9-51 airplanes; DC-9-81 (MD-81), DC-9-
82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87)
airplanes; and Model MD-88 airplanes.
----------------------------------------------------------------------------------------------------------------
Unsafe Condition
(d) This AD was prompted by a report of numerous cracked rudder
pedal brackets found during inspections of certain affected
airplanes. We are issuing this AD to prevent failure of the rudder
pedal bracket assembly, which could result in the loss of rudder and
braking control at either the captain's or first officer's position.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Requirements of AD 89-14-02
(f) Prior to the accumulation of 40,000 total landings or within
30 days after July 5, 1989 (the effective date of AD 89-14-02),
whichever occurs later, perform either a general visual inspection
or dye penetrant inspection for cracks of the captain's and first
officer's rudder pedal bracket, part numbers (P/N) 5616067 and
5616068, respectively, in accordance with McDonnell Douglas DC-8
Alert Service Bulletin A27-273 (for Model DC-8-11, DC-8-12, DC-8-21,
DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 airplanes;
Model DC-8-51, DC-8-52, DC-8-53, and DC-8-55 airplanes; Model DC-8F-
54 and DC-8F-55 airplanes; Model DC-8-61, DC-8-62, and DC-8-63
airplanes; Model DC-8-61F, DC-8-62F, and DC-8-63F airplanes; Model
DC-8-71, DC-8-72, and DC-8-73 airplanes), or McDonnell Douglas DC-9
Alert Service Bulletin A27-307 (for Model DC-9-11, DC-9-12, DC-9-13,
DC-9-14, DC-9-15, and DC-9-15F airplanes; Model DC-9-21 airplanes;
Model DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-
34, DC-9-34F, and DC-9-32F (C-9A, C-9B) airplanes; Model DC-9-41
airplanes; Model DC-9-51 airplanes; Model DC-9-81 (MD-81), DC-9-82
(MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; and Model
MD-88 airplanes), both Revision 1, both dated May 16, 1989, as
applicable.
Note 1: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or
droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''
Note 2: McDonnell Douglas DC-8 Alert Service Bulletin A27-273
and McDonnell Douglas DC-9 Alert Service Bulletin A27-307, both
Revision 1, both dated May 16, 1989, are hereinafter referred to as
ASB A27-273 and ASB A27-307, respectively.
(1) If an initial general visual inspection is accomplished, and
no cracks are found, perform a dye penetrant inspection of the
rudder pedal bracket assembly within 180 days after the general
visual inspection, and thereafter accomplish dye penetrant
inspections at intervals not to exceed 12 months or 2,500 landings,
whichever occurs earlier.
(2) If an initial dye penetrant inspection is accomplished, and
no cracks are found, accomplish repetitive dye penetrant inspections
at intervals not to exceed 12 months or 2,500 landings, whichever
occurs earlier.
(g) If cracks are detected, prior to further flight, remove and
replace the rudder pedal bracket assembly in accordance with ASB
A27-273 or A27-307, as applicable. Prior to the accumulation of
40,000 total landings after replacement with the new part, resume
the repetitive inspections in accordance with paragraph (f) in this
AD.
New Requirements of This AD
Terminating Action for Certain Airplanes
(h) For McDonnell Douglas Model DC-9-11, DC-9-12, DC-9-13, DC-9-
14, DC-9-15, and DC-9-15F airplanes; Model DC-9-21 airplanes; Model
DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-
9-34F, and DC-9-32F (C-9A, C-9B) airplanes; Model DC-9-41 airplanes;
Model DC-9-51 airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-
9-83 (MD-83), DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes:
Do the actions in paragraphs (h)(1) and (h)(2) of this AD in
accordance with the Accomplishment Instructions of McDonnell Douglas
DC-9 Alert Service Bulletin A27-307, Revision 4, dated June 3, 1991;
Revision 5, dated February 14, 1992; or Revision 6, dated December
19, 1994.
(1) Before the accumulation of 75,000 total landings on the
captain's rudder pedal bracket assembly, P/N 5616067-501, or within
60 months after the effective date of this AD, whichever occurs
later: Remove the rudder pedal bracket assembly and replace it with
new, improved P/N 5962903-501. Accomplishment of the replacement
terminates the repetitive inspections of the captain's rudder pedal
bracket assembly required by paragraphs (f) and (g) of this AD.
(2) Before the accumulation of 75,000 total landings on the
first officer's rudder pedal bracket assembly, P/N 5616068-501, or
within 60 months after the effective date of this AD, whichever
occurs later: Remove the rudder pedal bracket assembly and replace
it with new, improved P/N 5962904-501. Accomplishment of the
replacement terminates the repetitive inspections of the first
officer's rudder pedal bracket assembly required by paragraphs (f)
and (g) of this AD.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, Los Angeles Aircraft Certification Office,
FAA, has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with 14 CFR
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) AMOCs, approved previously in accordance with AD 89-14-02,
amendment 39-6245, are approved as AMOCs for the corresponding
requirements of this AD.
Material Incorporated by Reference
(j) You must use the applicable service information identified
in Table 2 of this AD to perform the actions that are required by
this AD, unless the AD specifies otherwise.
Table 2.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
McDonnell Douglas DC-8 Alert Service Bulletin A27- 1 May 16, 1989.
273.
[[Page 18205]]
McDonnell Douglas DC-9 Alert Service Bulletin A27- 1 May 16, 1989.
307.
McDonnell Douglas DC-9 Alert Service Bulletin A27- 4 June 3, 1991.
307.
McDonnell Douglas DC-9 Alert Service Bulletin A27- 5 February 14, 1992.
307.
McDonnell Douglas DC-9 Alert Service Bulletin A27- 6 December 19, 1994.
307.
----------------------------------------------------------------------------------------------------------------
McDonnell Douglas Alert Service Bulletin A27-307, Revision 6,
dated December 19, 1994, contains the following effective pages:
----------------------------------------------------------------------------------------------------------------
Revision level
Page Number shown on page Date shown on page
----------------------------------------------------------------------------------------------------------------
1-24.......................................... 6 December 19, 1994.
25-36......................................... 5 February 14, 1992.
----------------------------------------------------------------------------------------------------------------
The Director of the Federal Register approved the incorporation
by reference of these documents in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Contact Boeing Commercial Airplanes, Long Beach
Division, 3855 Lakewood Boulevard, Long Beach, California 90846,
Attention: Data and Service Management, Dept. C1-L5A (D800-0024),
for a copy of this service information. You may review copies at the
Docket Management Facility, U.S. Department of Transportation, 400
Seventh Street SW., room PL-401, Nassif Building, Washington, DC; on
the Internet at https://dms.dot.gov; or at the National Archives and
Records Administration (NARA). For information on the availability
of this material at the NARA, call (202) 741-6030, or go to https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on March 31, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-3380 Filed 4-10-06; 8:45 am]
BILLING CODE 4910-13-P
