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, 6578-6582 [E8-1813]
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Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Rules and Regulations
and Van Buren Counties, TN, to include
the entirety of each county.
Comments on the interim rule were
required to be received on or before
December 24, 2007. We did not receive
any comments. Therefore, for the
reasons given in the interim rule, we are
adopting the interim rule as a final rule.
This action also affirms the
information contained in the interim
rule regarding Executive Order 12866
and the Regulatory Flexibility Act,
Executive Orders 12372 and 12988, and
the Paperwork Reduction Act.
Further, for this action, the Office of
Management and Budget has waived its
review under Executive Order 12866.
List of Subjects in 7 CFR Part 301
Agricultural commodities, Plant
diseases and pests, Quarantine,
Reporting and recordkeeping
requirements, Transportation.
PART 301—DOMESTIC QUARANTINE
NOTICES
Accordingly, we are adopting as a
final rule, without change, the interim
rule that amended 7 CFR part 301 and
that was published at 72 FR 60533–
60537 on October 25, 2007.
I
Done in Washington, DC, this 30th day of
January 2008.
Kevin Shea,
Acting Administrator, Animal and Plant
Health Inspection Service.
[FR Doc. E8–2048 Filed 2–4–08; 8:45 am]
BILLING CODE 3410–34–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29061; Directorate
Identifier 2006–NM–243–AD; Amendment
39–15362; AD 2008–03–12]
RIN 2120–AA64
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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:
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SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain McDonnell
Douglas airplanes. The existing AD
currently requires an initial general
visual or dye penetrant inspection,
repetitive dye penetrant inspections,
and replacement, as necessary, of the
rudder pedal bracket. The existing AD
also currently requires, for certain
airplanes, replacing the rudder pedal
bracket assemblies with new, improved
parts, which would terminate the
repetitive inspections. For certain
airplanes, this new AD requires initial
inspection at a reduced threshold,
removes an inspection option, and
lengthens the repetitive inspection
intervals. This AD results from reports
of failures of the captain’s rudder pedal
brackets before reaching the initial
inspection threshold identified in the
existing AD. 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
March 11, 2008.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of March 11, 2008.
On May 16, 2006 (71 FR 18201, April
11, 2006), the Director of the Federal
Register approved the incorporation by
reference of certain other publications
listed in the AD.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Long Beach
Division, 3855 Lakewood Boulevard,
Long Beach, California 90846,
Attention: Data and Service
Management, Dept. C1–L5A (D800–
0024).
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Wahib Mina, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
PO 00000
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Angeles Aircraft Certification Office,
3960 Paramount Boulevard, Lakewood,
California 90712–4137; telephone (562)
627–5324; fax (562) 627–5210.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 2006–07–25, amendment
39–14552 (71 FR 18201, April 11, 2006).
The existing AD applies to certain
McDonnell Douglas airplanes. That
NPRM was published in the Federal
Register on August 31, 2007 (72 FR
50284). That NPRM proposed to retain
the requirements of AD 2006–07–25.
That NPRM also, for certain airplanes,
proposed to reduce certain initial
inspection thresholds, remove an
inspection option, and lengthen certain
repetitive inspection intervals.
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.
Request To Clarify Repetitive
Inspections
Air Transport Association (ATA), on
behalf of its member American Airlines,
requests that we clarify paragraphs (h)
and (l) of the NPRM. These paragraphs
specify repetitive inspections to
continue based on the part number of
the replaced rudder pedal bracket
assemblies in accordance with
paragraph (g) or (k) of the NPRM. The
commenters state that the referenced
rudder pedal bracket assemblies should
be clarified to indicate that repetitive
inspections apply only to rudder pedal
bracket assemblies that are of the same
part number as the ones inspected.
We agree with the request for the
reasons stated. The intent of the
replacement in paragraphs (h) and (l) of
the NPRM is to replace the rudder pedal
bracket assemblies with a part that has
the same part number as the part
inspected. Therefore, we have revised
paragraph (h) and (l) of the AD to
replace the words ‘‘new part’’ with
‘‘same part number as the one
inspected.’’
Request To Clarify Inspection Criteria
in Paragraph (j) of the NPRM
ATA, on behalf of its member ASTAR
Air Cargo, requests that we clarify the
inspection criteria in paragraph (j) of the
NPRM. The commenters note that
paragraph (j) of the NPRM specifies a
special detailed inspection in
accordance with McDonnell Douglas
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DC–8 Alert Service Bulletin A27–273,
Revision 1, dated May 16, 1989; or
Revision 5, dated February 18, 1993.
The commenters point out that the
service bulletins do not have any
inspection criteria listed.
We agree with the commenters that
the paragraph needs clarification. The
intent of paragraph (j) of the AD is to
specify a general visual inspection and
penetrant inspection for Category 2
airplanes in accordance with McDonnell
Douglas DC–8 Alert Service Bulletin
A27–273, Revision 1. Revision 1 of that
service bulletin contains the inspection
criteria. The intent of paragraph (j) was
to specify a special detailed inspection
for Category 4 airplanes in accordance
with Boeing Alert Service Bulletin DC9–
27A307, Revision 7, dated August 29,
2006. Revision 7 of that service bulletin
contains the inspection criteria. We
have revised paragraph (j) of the AD to
clarify the requirements.
Request To Clarify Compliance Time in
Paragraph (j)(1) of the NPRM
ATA, on behalf of its member ASTAR
Air Cargo, also notes that paragraph
(j)(1) of the NPRM specifies a
compliance time of within 40,000 total
landings or 30 days after the effective
date of the AD, whichever occurs later.
The commenters state that paragraph
(j)(1) should refer instead to 40,000 total
landings on the installed part.
We agree with the commenters.
McDonnell Douglas DC–8 Alert Service
Bulletin A27–273, Revision 1, and
Revision 5, specify a compliance time
based on the accumulation of 40,000
total landings on the bracket assembly.
We have revised paragraph (j)(1) of the
AD to specify that the compliance time
is 40,000 total landings on the installed
part.
6579
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 the economic burden
on any operator nor increase the scope
of the AD.
Costs of Compliance
There are about 1,840 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this AD. The replacements
are applicable only to 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.
ESTIMATED COSTS
Average
labor rate
per hour
Work
hours
Action
Parts
3
$80
None ......
5
80
None ......
$240, per inspection cycle.
$400, per inspection cycle.
9
80
$9,466 ....
$10,186 ................
Authority for This Rulemaking
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General visual inspection (required by
AD 2006–07–25).
Dye penetrant (special detailed) inspection (required by AD 2006–07–
25).
Replacements (required by AD 2006–
07–25).
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.
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
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
PO 00000
Frm 00003
Number of
U.S.registered
airplanes
Fleet cost
250 ..............
$60,000, per inspection cycle.
946 ..............
$378,400, per inspection
cycle.
up to 946 .....
up to $9,635,956.
Cost per airplane
Fmt 4700
Sfmt 4700
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
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 39–14552 (71
FR 18201, April 11, 2006) and by adding
the following new airworthiness
directive (AD):
I
2008–03–12 McDonnell Douglas:
Amendment 39–15362. Docket No.
FAA–2007–29061; Directorate Identifier
2006–NM–243–AD.
Effective Date
(a) This AD becomes effective March 11,
2008.
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Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Rules and Regulations
Affected ADs
Applicability
(c) This AD applies to the airplanes
identified in Table 1 of this AD, certificated
in any category.
(b) This AD supersedes AD 2006–07–25.
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–8–71F, DC–8–72F, and DC–8–73F 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; 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.
McDonnell Douglas DC–8 Alert Service Bulletin
A27–273, Revision 5, dated February 18,
1993.
Unsafe Condition
Service Information and Airplane Categories
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of the applicable service bulletin
identified in Table 2 of this AD. The term
‘‘airplane category,’’ as used in this AD,
means the category identified in Table 2 of
this AD.
(d) This AD results from reports of failures
of the captain’s rudder pedal brackets before
reaching the initial inspection threshold
identified in AD 2006–07–25. 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.
Boeing Alert Service Bulletin DC9–27A307, Revision 7, dated August 29, 2006.
TABLE 2.—SERVICE INFORMATION AND AIRPLANE CATEGORIES
Called airplane
category—
For Model—
(1) 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.
(2) DC–8–71F, DC–8–72F, and DC–8–73F airplanes ...................................
(3) 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.
(4) 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.
Requirements of AD 2006–07–25
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Initial Inspection Threshold
(g) For airplane categories 1, 3, and 4, 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, amendment
39–6245, which was superseded by AD
2006–07–25), whichever occurs later:
Perform either a general visual inspection,
dye penetrant inspection, or special detailed
inspection (eddy current with dye penetrant
or just dye penetrant), as applicable, for
cracking of the captain’s and first officer’s
rudder pedal bracket, part numbers (P/N)
5616067 and 5616068, respectively, in
accordance with the Accomplishment
Instructions of the applicable service bulletin
specified in Table 2 of this AD. After the
effective date of this AD, only the special
detailed inspection specified in Boeing Alert
Service Bulletin DC9–27A307, Revision 7,
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1
2
3
Use—
McDonnell Douglas DC–8 Alert Service Bulletin
A27–273, Revision 1, dated May 16, 1989; or
Revision 5, dated February 18, 1993.
McDonnell Douglas DC–9 Alert Service Bulletin
A27–307, Revision 1, dated May 16, 1989; or
Boeing Alert Service Bulletin DC9–27A307, Revision 7, dated August 29, 2006, after the effective date of this AD, only Revision 7 may be
used.
4
dated August 29, 2006, may be used for
airplanes identified in Revision 7. For
airplane category 4: Do the inspection
required by this paragraph until the
inspection required by paragraph (j) of this
AD is accomplished.
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.’’
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(1) If an initial general visual inspection is
accomplished, and no crack is 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. For airplane categories 3 and 4, repeat
at this interval until the inspection required
by paragraph (k) of this AD is accomplished.
(2) If an initial dye penetrant inspection is
accomplished, and no crack is found,
accomplish repetitive dye penetrant
inspections at intervals not to exceed 12
months or 2,500 landings, whichever occurs
earlier. For airplane categories 3 and 4, repeat
at this interval until the inspection required
by paragraph (k) of this AD is accomplished.
(3) If an initial special detailed inspection
is accomplished after the effective date of
this AD, and no crack is found, repeat the
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inspection in accordance with paragraph (k)
of this AD.
Corrective Action
(h) Except as provided by paragraph (l) of
this AD: If any crack is detected during any
inspection required by paragraph (g) or (j) of
this AD, before further flight, remove and
replace the rudder pedal bracket assembly in
accordance with the service bulletin. Prior to
the accumulation of 40,000 total landings
after replacement with a part that has the
same number as the part inspected, resume
the repetitive inspections in accordance with
paragraph (g) or (k) of this AD, as applicable.
Doing the action required by paragraph (l) of
this AD terminates the requirements of this
paragraph for airplane category 4.
Terminating Action for Certain Airplanes
(i) For airplane categories 3 and 4: Do the
actions in paragraphs (i)(1) and (i)(2) of this
AD in accordance with the Accomplishment
Instructions of the applicable service bulletin
specified in Table 2 of this AD.
(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 May 16, 2006,
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 (g), (h), (j), (k), and (l)
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 May 16, 2006,
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 (g), (h), (j), (k), and (l)
of this AD.
New Requirements of This AD
Revised Initial Inspection at Reduced
Threshold for Certain Airplanes
(j) For airplane categories 2 and 4, at the
applicable time specified in paragraph (j)(1),
(j)(2) or (j)(3) of this AD: Do a general visual
and penetrant inspection (for airplane
category 2), and a special detailed inspection
(for airplane category 4), as applicable, to
detect cracking of the captain’s and first
officer’s rudder pedal bracket, part numbers
(P/N) 5616067 and 5616068, respectively, in
accordance with the applicable service
bulletin specified in Table 2 of this AD.
Procedures for the dye penetrant inspection
for airplane category 2 are contained only in
the Accomplishment Instructions of
McDonnell Douglas DC–8 Alert Service
Bulletin A27–273, Revision 1, dated May 16,
1989. Procedures for the special detailed
inspection are contained in Boeing Alert
Service Bulletin DC9–27A307, Revision 7,
dated August 29, 2006. Doing the applicable
inspection required by this paragraph
terminates the inspection requirements of
paragraphs (g) and (h) of this AD for airplane
category 4.
(1) For category 2 airplanes: Before the
accumulation of 40,000 total landings on the
installed part, or within 30 days after the
effective date of this AD, whichever occurs
later.
(2) For category 4 airplanes that have
accumulated fewer than 25,000 total landings
as of the effective date of this AD: Before the
accumulation of 25,000 total landings, or
within 3,000 landings after the effective date
of this AD, whichever occurs later.
(3) For category 4 airplanes that have
accumulated 25,000 or more total landings as
of the effective date of this AD, do the next
inspection at the applicable time in
paragraph (j)(3)(i) or (j)(3)(ii) of this AD.
(i) For category 4 airplanes on which the
corrective action specified in paragraph (h) of
this AD has not been accomplished, do the
inspection within 3,000 landings after the
effective date of this AD.
(ii) For category 4 airplanes on which the
corrective action required by paragraph (h) of
this AD has been accomplished, do the
inspection at the earlier of the following: The
next repetitive interval required by paragraph
(h) of this AD; 40,000 total landings after
doing the corrective action required by
paragraph (h) of this AD; or 3,000 landings
after the effective date of this AD.
paragraph (g) or (j) of this AD thereafter at
intervals not to exceed 3,000 landings. Doing
the first repetitive inspection required by this
paragraph terminates the repetitive
inspection requirements of paragraph (g) of
this AD for airplane categories 3 and 4.
Repetitive Inspections at Revised Interval
for Certain Airplanes
(k) For airplane categories 3 and 4: Repeat
the special detailed inspection required by
(n) You must use the service information
listed in Table 3 of this AD to perform the
actions that are required by this AD, unless
the AD specifies otherwise.
Corrective Action Including Reduced
Inspection Threshold for Certain Airplanes
(l) For airplane category 4: If any crack is
detected during any inspection required by
paragraph (g), (j), or (k) of this AD: Before
further flight, remove and replace the rudder
pedal bracket assembly with a part that has
the same part number as the one inspected,
in accordance with the applicable service
bulletin specified in Table 2 of this AD.
Before the accumulation of 25,000 total
landings after replacement, resume the
repetitive inspections in accordance with
paragraph (k) of this AD. Doing the action in
this paragraph terminates the requirements of
paragraph (h) of this AD for airplane category
4.
Alternative Methods of Compliance
(AMOCs)
(m)(1) The Manager, Los Angeles Aircraft
Certification Office, 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) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(3) AMOCs, approved previously in
accordance with AD 2006–07–25,
amendment 39–14552; and AD 89–14–02,
amendment 39–6245; are approved as
AMOCs for the corresponding requirements
of this AD.
Material Incorporated by Reference
TABLE 3.—ALL MATERIAL INCORPORATED BY REFERENCE
Revision
level
Service Bulletin
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McDonnell Douglas DC–8 Alert Service Bulletin A27–273 .............................................................................
McDonnell Douglas DC–8 Alert Service Bulletin A27–273 .............................................................................
McDonnell Douglas DC–9 Alert Service Bulletin A27–307 .............................................................................
Boeing Alert Service bulletin DC9-27A307 .....................................................................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
McDonnell Douglas DC–8 Alert Service
Bulletin A27–273, Revision 5, dated February
18, 1993; and Boeing Alert Service Bulletin
DC9–27A307, Revision 7, dated August 29,
2006; in accordance with 5 U.S.C. 552(a) and
1 CFR part 51.
VerDate Aug<31>2005
15:28 Feb 04, 2008
Jkt 214001
(2) On May 16, 2006 (71 FR 18201, April
11, 2006), the Director of the Federal Register
approved the incorporation by reference of
McDonnell Douglas DC–8 Alert Service
Bulletin A27–273, Revision 1, dated May 16,
1989; and McDonnell Douglas DC–9 Alert
Service Bulletin A27–307, Revision 1, dated
May 16, 1989.
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
Date
1
5
1
7
May 16, 1989.
February 18, 1993.
May 16, 1989.
August 29, 2006.
(3) 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 FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, Washington;
E:\FR\FM\05FER1.SGM
05FER1
6582
Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Rules and Regulations
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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on January
24, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–1813 Filed 2–4–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28956; Directorate
Identifier 2007–CE–068–AD; Amendment
39–15360; AD 2008–03–10]
RIN 2120–AA64
Airworthiness Directives; Cessna
Aircraft Company Models 525, 525A,
and 525B Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
Cessna Aircraft Company (Cessna)
Models 525, 525A, and 525B airplanes.
This AD requires you to inspect the
lower wing skin structure, forward wing
spar, lower fuselage skin, fairings, and
the external fairing frames for corrosion;
repair any damage found; apply a
corrosion inhibitive sealant to the
fuselage fairings before reinstalling; and
disable the cockpit mounted pilot relief
tube. This AD results from leaking of the
cockpit mounted pilot relief tube, which
caused corrosion of the airplane
structure. We are issuing this AD to
detect and correct any damage from
corrosion of the airplane structure.
Corrosion of the airplane structure
could cause structural degradation and
lead to structural failure of the airplane
with consequent loss of control.
DATES: This AD becomes effective on
March 11, 2008.
On March 11, 2008, the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: For service information
identified in this AD, contact Cessna
Aircraft Company, Citation Marketing
Division, P.O. Box 7706, Wichita,
Kansas 67277; telephone: 1–800–835–
4090; fax: 1–800–517–8500.
To view the AD docket, go to U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590, or on the Internet at https://
www.regulations.gov. The docket
number is FAA–2007–28956;
Directorate Identifier 2007–CE–068–AD.
FOR FURTHER INFORMATION CONTACT: T.N.
Baktha, Aerospace Engineer,1801
Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946–
4155; fax: (316) 946–4107.
SUPPLEMENTARY INFORMATION:
include an AD that would apply to
certain Cessna Models 525, 525A, and
525B airplanes. This proposal was
published in the Federal Register as a
notice of proposed rulemaking (NPRM)
on October 26, 2007 (72 FR 60790). The
NPRM proposed to require you to
inspect the lower wing skin structure,
forward wing spar, lower fuselage skin,
fairings, and the external fairing frames
for corrosion; repair any damage found;
apply a corrosion inhibitive sealant to
the fuselage fairings before reinstalling;
and disable the cockpit mounted pilot
relief tube.
Discussion
On October 22, 2007, we issued a
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
We estimate that this AD affects 261
airplanes in the U.S. registry.
We estimate the following costs to do
the inspection:
Comments
We provided the public the
opportunity to participate in developing
this AD. We received no comments on
the proposal or on the determination of
the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed except for
minor editorial corrections. We have
determined that these minor
corrections:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Costs of Compliance
Labor cost
Parts cost
Total cost per
airplane
Total cost on
U.S. operators
80 work-hours × $80 per hour = $6,400 ...................................................
Not applicable ..................................
$6,400
$1,670,400
We have no way of determining the
number of airplanes that may need
repair or further inspection based on the
results of the inspection, or the costs
associated with such repair or
inspection.
We estimate the following costs to
disable the cockpit mounted pilot relief
tube:
Parts cost
Total cost per
airplane
Total cost on
U.S. operators
.5 work-hour × $80 per hour = $40 ...........................................................
rmajette on PROD1PC64 with RULES
Labor cost
Not applicable ..................................
$40
$10,440
Cessna will provide warranty credit to
the extent specified in Cessna Citation
Service Bulletin SB525–53–20, dated
April 30, 2007; Cessna Citation Service
Bulletin SB525A–53–01, dated April 30,
2007; Cessna Citation Service Bulletin
SB525B–53–01, dated April 30, 2007;
Cessna Citation Alert Service Letter
VerDate Aug<31>2005
15:28 Feb 04, 2008
Jkt 214001
ASL525–53–04, Revision 2, dated
August 19, 2007; Cessna Citation Alert
Service Letter ASL525A–53–05,
Revision 2, dated July 25, 2007; and
Cessna Citation Alert Service Letter
ASL525B–53–02, Revision 2, dated July
25, 2007.
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
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
E:\FR\FM\05FER1.SGM
05FER1
]]>Agencies
[Federal Register Volume 73, Number 24 (Tuesday, February 5, 2008)]
[Rules and Regulations]
[Pages 6578-6582]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-1813]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29061; Directorate Identifier 2006-NM-243-AD;
Amendment 39-15362; AD 2008-03-12]
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. The
existing AD currently requires an initial general visual or dye
penetrant inspection, repetitive dye penetrant inspections, and
replacement, as necessary, of the rudder pedal bracket. The existing AD
also currently requires, for certain airplanes, replacing the rudder
pedal bracket assemblies with new, improved parts, which would
terminate the repetitive inspections. For certain airplanes, this new
AD requires initial inspection at a reduced threshold, removes an
inspection option, and lengthens the repetitive inspection intervals.
This AD results from reports of failures of the captain's rudder pedal
brackets before reaching the initial inspection threshold identified in
the existing AD. 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 March 11, 2008.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of March 11,
2008.
On May 16, 2006 (71 FR 18201, April 11, 2006), the Director of the
Federal Register approved the incorporation by reference of certain
other publications listed in the AD.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood
Boulevard, Long Beach, California 90846, Attention: Data and Service
Management, Dept. C1-L5A (D800-0024).
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
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:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 2006-07-25, amendment
39-14552 (71 FR 18201, April 11, 2006). The existing AD applies to
certain McDonnell Douglas airplanes. That NPRM was published in the
Federal Register on August 31, 2007 (72 FR 50284). That NPRM proposed
to retain the requirements of AD 2006-07-25. That NPRM also, for
certain airplanes, proposed to reduce certain initial inspection
thresholds, remove an inspection option, and lengthen certain
repetitive inspection intervals.
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.
Request To Clarify Repetitive Inspections
Air Transport Association (ATA), on behalf of its member American
Airlines, requests that we clarify paragraphs (h) and (l) of the NPRM.
These paragraphs specify repetitive inspections to continue based on
the part number of the replaced rudder pedal bracket assemblies in
accordance with paragraph (g) or (k) of the NPRM. The commenters state
that the referenced rudder pedal bracket assemblies should be clarified
to indicate that repetitive inspections apply only to rudder pedal
bracket assemblies that are of the same part number as the ones
inspected.
We agree with the request for the reasons stated. The intent of the
replacement in paragraphs (h) and (l) of the NPRM is to replace the
rudder pedal bracket assemblies with a part that has the same part
number as the part inspected. Therefore, we have revised paragraph (h)
and (l) of the AD to replace the words ``new part'' with ``same part
number as the one inspected.''
Request To Clarify Inspection Criteria in Paragraph (j) of the NPRM
ATA, on behalf of its member ASTAR Air Cargo, requests that we
clarify the inspection criteria in paragraph (j) of the NPRM. The
commenters note that paragraph (j) of the NPRM specifies a special
detailed inspection in accordance with McDonnell Douglas
[[Page 6579]]
DC-8 Alert Service Bulletin A27-273, Revision 1, dated May 16, 1989; or
Revision 5, dated February 18, 1993. The commenters point out that the
service bulletins do not have any inspection criteria listed.
We agree with the commenters that the paragraph needs
clarification. The intent of paragraph (j) of the AD is to specify a
general visual inspection and penetrant inspection for Category 2
airplanes in accordance with McDonnell Douglas DC-8 Alert Service
Bulletin A27-273, Revision 1. Revision 1 of that service bulletin
contains the inspection criteria. The intent of paragraph (j) was to
specify a special detailed inspection for Category 4 airplanes in
accordance with Boeing Alert Service Bulletin DC9-27A307, Revision 7,
dated August 29, 2006. Revision 7 of that service bulletin contains the
inspection criteria. We have revised paragraph (j) of the AD to clarify
the requirements.
Request To Clarify Compliance Time in Paragraph (j)(1) of the NPRM
ATA, on behalf of its member ASTAR Air Cargo, also notes that
paragraph (j)(1) of the NPRM specifies a compliance time of within
40,000 total landings or 30 days after the effective date of the AD,
whichever occurs later. The commenters state that paragraph (j)(1)
should refer instead to 40,000 total landings on the installed part.
We agree with the commenters. McDonnell Douglas DC-8 Alert Service
Bulletin A27-273, Revision 1, and Revision 5, specify a compliance time
based on the accumulation of 40,000 total landings on the bracket
assembly. We have revised paragraph (j)(1) of the AD to specify that
the compliance time is 40,000 total landings on the installed part.
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
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
There are about 1,840 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this AD. The replacements are applicable
only to 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.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Average
Work labor Number of U.S.-
Action hours rate per Parts Cost per airplane registered airplanes Fleet cost
hour
--------------------------------------------------------------------------------------------------------------------------------------------------------
General visual inspection (required 3 $80 None............... $240, per inspection 250.................... $60,000, per
by AD 2006-07-25). cycle. inspection cycle.
Dye penetrant (special detailed) 5 80 None............... $400, per inspection 946.................... $378,400, per
inspection (required by AD 2006-07- cycle. inspection cycle.
25).
Replacements (required by AD 2006-07- 9 80 $9,466............. $10,186............... up to 946.............. up to $9,635,956.
25).
--------------------------------------------------------------------------------------------------------------------------------------------------------
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 39-14552 (71 FR 18201, April 11, 2006) and by adding
the following new airworthiness directive (AD):
2008-03-12 McDonnell Douglas: Amendment 39-15362. Docket No. FAA-
2007-29061; Directorate Identifier 2006-NM-243-AD.
Effective Date
(a) This AD becomes effective March 11, 2008.
[[Page 6580]]
Affected ADs
(b) This AD supersedes AD 2006-07-25.
Applicability
(c) This AD applies to the airplanes identified in Table 1 of
this AD, certificated in any category.
Table 1.--Applicability
------------------------------------------------------------------------
McDonnell Douglas-- As identified in--
------------------------------------------------------------------------
Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, McDonnell Douglas DC-8 Alert
DC-8-32, DC-8-33, DC-8-41, DC-8-42, and Service Bulletin A27-273,
DC-8-43 airplanes; Model DC-8-51, DC-8- Revision 5, dated February
52, DC-8-53, and DC-8-55 airplanes; Model 18, 1993.
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-8-71F, DC-8-72F,
and DC-8-73F airplanes.
Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, Boeing Alert Service
DC-9-15, and DC-9-15F airplanes; Model DC- Bulletin DC9-27A307,
9-21 airplanes; Model DC-9-31, DC-9-32, Revision 7, dated August
DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9- 29, 2006.
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.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from reports of failures of the captain's
rudder pedal brackets before reaching the initial inspection
threshold identified in AD 2006-07-25. 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.
Service Information and Airplane Categories
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of the applicable service bulletin
identified in Table 2 of this AD. The term ``airplane category,'' as
used in this AD, means the category identified in Table 2 of this
AD.
Table 2.--Service Information and Airplane Categories
------------------------------------------------------------------------
Called
For Model-- airplane Use--
category--
------------------------------------------------------------------------
(1) DC-8-11, DC-8-12, DC-8-21, 1 McDonnell Douglas DC-8
DC-8-31, DC-8-32, DC-8-33, DC-8- Alert Service
41, DC-8-42, and DC-8-43 Bulletin A27-273,
airplanes; Model DC-8-51, DC-8- Revision 1, dated May
52, DC-8-53, and DC-8-55 16, 1989; or Revision
airplanes; Model DC-8F-54 and 5, dated February 18,
DC-8F-55 airplanes; Model DC-8- 1993.
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.
(2) DC-8-71F, DC-8-72F, and DC-8- 2
73F airplanes.
(3) DC-9-11, DC-9-12, DC-9-13, 3 McDonnell Douglas DC-9
DC-9-14, DC-9-15, and DC-9-15F Alert Service
airplanes; Model DC-9-21 Bulletin A27-307,
airplanes; Model DC-9-31, DC-9- Revision 1, dated May
32, DC-9-32 (VC-9C), DC-9-32F, 16, 1989; or Boeing
DC-9-33F, DC-9-34, DC-9-34F, Alert Service
and DC-9-32F (C-9A, C-9B) Bulletin DC9-27A307,
airplanes; Model DC-9-41 Revision 7, dated
airplanes; Model DC-9-51 August 29, 2006,
airplanes. after the effective
date of this AD, only
Revision 7 may be
used.
(4) DC-9-81 (MD-81), DC-9-82 (MD- 4
82), DC-9-83 (MD-83), and DC-9-
87 (MD-87) airplanes; and Model
MD-88 airplanes.
------------------------------------------------------------------------
Requirements of AD 2006-07-25
Initial Inspection Threshold
(g) For airplane categories 1, 3, and 4, 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, amendment 39-6245, which
was superseded by AD 2006-07-25), whichever occurs later: Perform
either a general visual inspection, dye penetrant inspection, or
special detailed inspection (eddy current with dye penetrant or just
dye penetrant), as applicable, for cracking of the captain's and
first officer's rudder pedal bracket, part numbers (P/N) 5616067 and
5616068, respectively, in accordance with the Accomplishment
Instructions of the applicable service bulletin specified in Table 2
of this AD. After the effective date of this AD, only the special
detailed inspection specified in Boeing Alert Service Bulletin DC9-
27A307, Revision 7, dated August 29, 2006, may be used for airplanes
identified in Revision 7. For airplane category 4: Do the inspection
required by this paragraph until the inspection required by
paragraph (j) of this AD is accomplished.
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.''
(1) If an initial general visual inspection is accomplished, and
no crack is 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. For airplane categories 3 and 4, repeat at this
interval until the inspection required by paragraph (k) of this AD
is accomplished.
(2) If an initial dye penetrant inspection is accomplished, and
no crack is found, accomplish repetitive dye penetrant inspections
at intervals not to exceed 12 months or 2,500 landings, whichever
occurs earlier. For airplane categories 3 and 4, repeat at this
interval until the inspection required by paragraph (k) of this AD
is accomplished.
(3) If an initial special detailed inspection is accomplished
after the effective date of this AD, and no crack is found, repeat
the
[[Page 6581]]
inspection in accordance with paragraph (k) of this AD.
Corrective Action
(h) Except as provided by paragraph (l) of this AD: If any crack
is detected during any inspection required by paragraph (g) or (j)
of this AD, before further flight, remove and replace the rudder
pedal bracket assembly in accordance with the service bulletin.
Prior to the accumulation of 40,000 total landings after replacement
with a part that has the same number as the part inspected, resume
the repetitive inspections in accordance with paragraph (g) or (k)
of this AD, as applicable. Doing the action required by paragraph
(l) of this AD terminates the requirements of this paragraph for
airplane category 4.
Terminating Action for Certain Airplanes
(i) For airplane categories 3 and 4: Do the actions in
paragraphs (i)(1) and (i)(2) of this AD in accordance with the
Accomplishment Instructions of the applicable service bulletin
specified in Table 2 of this AD.
(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 May 16, 2006, 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 (g), (h), (j), (k), and (l) 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 May 16, 2006, 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 (g), (h), (j), (k), and (l) of this
AD.
New Requirements of This AD
Revised Initial Inspection at Reduced Threshold for Certain Airplanes
(j) For airplane categories 2 and 4, at the applicable time
specified in paragraph (j)(1), (j)(2) or (j)(3) of this AD: Do a
general visual and penetrant inspection (for airplane category 2),
and a special detailed inspection (for airplane category 4), as
applicable, to detect cracking of the captain's and first officer's
rudder pedal bracket, part numbers (P/N) 5616067 and 5616068,
respectively, in accordance with the applicable service bulletin
specified in Table 2 of this AD. Procedures for the dye penetrant
inspection for airplane category 2 are contained only in the
Accomplishment Instructions of McDonnell Douglas DC-8 Alert Service
Bulletin A27-273, Revision 1, dated May 16, 1989. Procedures for the
special detailed inspection are contained in Boeing Alert Service
Bulletin DC9-27A307, Revision 7, dated August 29, 2006. Doing the
applicable inspection required by this paragraph terminates the
inspection requirements of paragraphs (g) and (h) of this AD for
airplane category 4.
(1) For category 2 airplanes: Before the accumulation of 40,000
total landings on the installed part, or within 30 days after the
effective date of this AD, whichever occurs later.
(2) For category 4 airplanes that have accumulated fewer than
25,000 total landings as of the effective date of this AD: Before
the accumulation of 25,000 total landings, or within 3,000 landings
after the effective date of this AD, whichever occurs later.
(3) For category 4 airplanes that have accumulated 25,000 or
more total landings as of the effective date of this AD, do the next
inspection at the applicable time in paragraph (j)(3)(i) or
(j)(3)(ii) of this AD.
(i) For category 4 airplanes on which the corrective action
specified in paragraph (h) of this AD has not been accomplished, do
the inspection within 3,000 landings after the effective date of
this AD.
(ii) For category 4 airplanes on which the corrective action
required by paragraph (h) of this AD has been accomplished, do the
inspection at the earlier of the following: The next repetitive
interval required by paragraph (h) of this AD; 40,000 total landings
after doing the corrective action required by paragraph (h) of this
AD; or 3,000 landings after the effective date of this AD.
Repetitive Inspections at Revised Interval for Certain Airplanes
(k) For airplane categories 3 and 4: Repeat the special detailed
inspection required by paragraph (g) or (j) of this AD thereafter at
intervals not to exceed 3,000 landings. Doing the first repetitive
inspection required by this paragraph terminates the repetitive
inspection requirements of paragraph (g) of this AD for airplane
categories 3 and 4.
Corrective Action Including Reduced Inspection Threshold for Certain
Airplanes
(l) For airplane category 4: If any crack is detected during any
inspection required by paragraph (g), (j), or (k) of this AD: Before
further flight, remove and replace the rudder pedal bracket assembly
with a part that has the same part number as the one inspected, in
accordance with the applicable service bulletin specified in Table 2
of this AD. Before the accumulation of 25,000 total landings after
replacement, resume the repetitive inspections in accordance with
paragraph (k) of this AD. Doing the action in this paragraph
terminates the requirements of paragraph (h) of this AD for airplane
category 4.
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, Los Angeles Aircraft Certification Office,
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) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(3) AMOCs, approved previously in accordance with AD 2006-07-25,
amendment 39-14552; and AD 89-14-02, amendment 39-6245; are approved
as AMOCs for the corresponding requirements of this AD.
Material Incorporated by Reference
(n) You must use the service information listed in Table 3 of
this AD to perform the actions that are required by this AD, unless
the AD specifies otherwise.
Table 3.--All Material Incorporated by Reference
------------------------------------------------------------------------
Revision
Service Bulletin level Date
------------------------------------------------------------------------
McDonnell Douglas DC-8 Alert 1 May 16, 1989.
Service Bulletin A27-273.
McDonnell Douglas DC-8 Alert 5 February 18, 1993.
Service Bulletin A27-273.
McDonnell Douglas DC-9 Alert 1 May 16, 1989.
Service Bulletin A27-307.
Boeing Alert Service bulletin 7 August 29, 2006.
DC9-27A307.
------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of McDonnell Douglas DC-8 Alert Service
Bulletin A27-273, Revision 5, dated February 18, 1993; and Boeing
Alert Service Bulletin DC9-27A307, Revision 7, dated August 29,
2006; in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) On May 16, 2006 (71 FR 18201, April 11, 2006), the Director
of the Federal Register approved the incorporation by reference of
McDonnell Douglas DC-8 Alert Service Bulletin A27-273, Revision 1,
dated May 16, 1989; and McDonnell Douglas DC-9 Alert Service
Bulletin A27-307, Revision 1, dated May 16, 1989.
(3) 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 FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington;
[[Page 6582]]
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: https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued in Renton, Washington, on January 24, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-1813 Filed 2-4-08; 8:45 am]
BILLING CODE 4910-13-P
