Airworthiness Directives; McDonnell Douglas Model DC-9-14, DC-9-15, and DC-9-15F Airplanes; and McDonnell Douglas Model DC-9-20, DC-9-30, DC-9-40, and DC-9-50 Series Airplanes, 63578-63581 [E9-28564]
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Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations
pump wiring to provide protection against
chafing of the fuel pump cables. This
condition, if not corrected, could generate
short circuits leading to fuel pump failure
and arcing. These could become a potential
ignition source inside the fuel tank which, in
combination with flammable fuel vapours (if
present), could result in a fuel tank explosion
and consequent loss of the aeroplane.
To address this unsafe condition, EASA
[European Aviation Safety Agency] issued
AD 2007–0066 that required this
modification in accordance with Airbus
Service Bulletin (SB) A300–24–0103
Revision 01. Airbus subsequently introduced
an additional modification of the electrical
wiring of the outer fuel pump and the
landing lights of the left (LH) and the right
(RH) side in Revision 02 of the SB A300–24–
0103, leading to the issuance of EASA AD
2008–0188 which superseded EASA AD
2007–0066 and required the additional work.
More recently, Airbus introduced some
additional protection to routes 1P and 2P
harnesses in zone 571 and 671 of the
aeroplane.
For the reason described above, this new
AD retains the requirements of EASA AD
2008–0188, which is superseded, and
requires the additional work as specified in
Revision 03 of Airbus SB A300–24–0103.
The additional modification will provide
additional protection from chafing and will
prevent intermittent operation of the fuel
pump and landing lights, as well as failure
of the power supply. The modification of the
wiring of the outer fuel pump and the
landing light on the LH side route 1P harness
and RH side route 2P harness includes
additional mechanical protection that
includes procedures for installing new
splicing on the wires, a new cable type,
shrink sleeve installation on the new wiring,
and an additional braided conduit sleeve
(Halar), as applicable, for the fuel pumps and
the landing lights.
jlentini on DSKJ8SOYB1PROD with RULES
Restatement of Requirements of AD 2007–
18–02, With Revised Service Information
(f) Within 31 months after October 2, 2007
(the effective date of AD 2007–18–02), unless
already done, modify the inner and outer fuel
pump wiring, route 1P and 2P harnesses in
the LH (left-hand) wing and in the RH (righthand) wing, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–24–0103, Revision 01,
dated January 11, 2007; or Airbus Mandatory
Service Bulletin A300–24–0103, Revision 03,
dated February 18, 2009. After the effective
date of this AD, use only Airbus Mandatory
Service Bulletin A300–24–0103, Revision 03,
dated February 18, 2009. Actions done before
October 2, 2007, in accordance with Airbus
Service Bulletin A300–24–0103, dated March
15, 2006, for airplanes under configuration 1
as defined in Airbus Service Bulletin A300–
24–0103, Revision 01, dated January 11,
2007; Revision 02, dated April 4, 2008; or
Revision 03, dated February 18, 2009; are
acceptable for compliance with the
requirements of this paragraph.
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17:09 Dec 03, 2009
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New Requirements of This AD
Actions and Compliance
(g) Unless already done, within 12 months
after the effective date of this AD, modify the
wiring of the outer fuel pump and the
landing light on the LH side route 1P harness
and RH side route 2P harness in accordance
with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A300–24–
0103, Revision 03, dated February 18, 2009.
FAA AD Differences
Note 1: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(h) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Dan Rodina,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–2125; fax (425) 227–1149. 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. AMOCs
approved previously in accordance with AD
2007–18–02, are approved as AMOCs for the
corresponding provisions of this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(i) Refer to MCAI EASA Airworthiness
Directive 2009–0157, dated July 17, 2009;
Airbus Service Bulletin A300–24–0103,
Revision 01, dated January 11, 2007; and
Airbus Mandatory Service Bulletin A300–24–
0103, Revision 03, dated February 18, 2009;
for related information.
Material Incorporated by Reference
(j) You must use Airbus Mandatory Service
Bulletin A300–24–0103, Revision 03, dated
February 18, 2009, to do the actions required
by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
PO 00000
Frm 00048
Fmt 4700
Sfmt 4700
(2) For service information identified in
this AD, contact Airbus SAS—EAW
(Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; e-mail: account.airwortheas@airbus.com; Internet https://
www.airbus.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
reference 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/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
November 23, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–28797 Filed 12–3–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0658; Directorate
Identifier 2009–NM–058–AD; Amendment
39–16115; AD 2009–24–21]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model DC–9–14, DC–9–15,
and DC–9–15F Airplanes; and
McDonnell Douglas Model DC–9–20,
DC–9–30, DC–9–40, and DC–9–50
Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD)
that applies to all McDonnell Douglas
Model DC–9–14, DC–9–15, and DC–9–
15F airplanes; and McDonnell Douglas
Model DC–9–20, DC–9–30, DC–9–40,
and DC–9–50 series airplanes. That AD
currently requires repetitive inspections
for cracks of the main landing gear
(MLG) shock strut cylinder, and related
investigative and corrective actions if
necessary. This AD adds more work on
airplanes that have main landing gear
shock struts with certain identified part
numbers. This AD results from two
reports of a collapsed MLG and a report
of cracks in two MLG cylinders. We are
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Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations
issuing this AD to detect and correct
fatigue cracks in the shock strut cylinder
of the MLG, which could result in a
collapsed MLG during takeoff or
landing, and possible reduced structural
integrity of the airplane.
DATES: This AD becomes effective
January 8, 2010.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of January 8, 2010.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, 3855
Lakewood Boulevard, MC D800–0019,
Long Beach, California 90846–0001;
telephone 206–544–5000, extension 2;
fax 206–766–5683; e-mail
dse.boecom@boeing.com; Internet
https://www.myboeingfleet.com.
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
63579
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.
That NPRM proposed to continue to
require repetitive inspections for cracks
of the main landing gear (MLG) shock
strut cylinder, and related investigative
and corrective actions if necessary. That
NPRM also proposed to require more
work on airplanes that have main
landing gear shock struts with certain
identified part numbers.
FOR FURTHER INFORMATION CONTACT:
Wahib Mina, ANM–120L, FAA, Los
Angeles Aircraft Certification Office,
3960 Paramount Boulevard, Lakewood,
California 90712–4137; telephone (562)
627–5324; fax (562) 627–5210.
Comments
SUPPLEMENTARY INFORMATION:
Discussion
We provided the public the
opportunity to participate in the
development of this AD. No comments
have been received on the NPRM or on
the determination of the cost to the
public.
Conclusion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 2005–19–08, amendment
39–14273 (70 FR 54616, September 16,
2005). The existing AD applies to all
McDonnell Douglas Model DC–9–14,
DC–9–15, and DC–9–15F airplanes; and
Model DC–9–20, DC–9–30, DC–9–40,
and DC–9–50 series airplanes. That
NPRM was published in the Federal
Register on July 30, 2009 (74 FR 37963).
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed.
Costs of Compliance
There are about 644 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.
ESTIMATED COSTS
Action
Work hours
Inspection ...............
Average
labor rate
per hour
4 to 6 .....................
$80
Parts
None .....................
$320 to $480 per
inspection cycle.
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Authority for This Rulemaking
Regulatory Findings
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.
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.
VerDate Nov<24>2008
17:09 Dec 03, 2009
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PO 00000
Number of
U.S.registered
airplanes
Cost per airplane
Frm 00049
Fmt 4700
Sfmt 4700
426
Fleet cost
$136,320 to $204,480 per
inspection cycle.
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
Accordingly, under the authority
delegated to me by the Administrator,
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:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–14273 (70
FR 54616, September 16, 2005) and by
■
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Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations
adding the following new airworthiness
directive (AD):
2009–24–21 McDonnell Douglas:
Amendment 39–16115. Docket No.
FAA–2009–0658; Directorate Identifier
2009–NM–058–AD.
are issuing this AD to detect and correct
fatigue cracks in the shock strut cylinder of
the MLG, which could result in a collapsed
MLG during takeoff or landing, and possible
reduced structural integrity of the airplane.
Compliance
Effective Date
(a) This AD becomes effective January 8,
2010.
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Affected ADs
(b) This AD supersedes AD 2005–19–08.
Restatement of Requirements of AD 2005–
19–08, With Revised Service Information
Applicability
(c) This AD applies to all McDonnell
Douglas Model 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; and Model DC–9–
51 airplanes; certificated in any category.
Subject
(d) Air Transport Association (ATA) of
America Code 32: Landing gear.
Unsafe Condition
(e) This AD results from two reports of a
collapsed main landing gear (MLG) and a
report of cracks in two MLG cylinders. We
Records Review
(g) Except as required by paragraph (m) of
this AD, before the applicable compliance
time specified in paragraph (h) or Table 1 of
this AD, as applicable, do the applicable
actions in paragraphs (g)(1) and (g)(2) of this
AD.
(1) For all airplane groups: Review the
airplane maintenance records of the MLG to
determine its service history and the number
of landings on the MLG shock strut cylinder.
(2) For Group 3 airplanes identified in the
service bulletin: Review the maintenance
records to determine if the MLG cylinder on
each Group 3 airplane has always been on a
Group 3 airplane, and do the actions in
paragraph (k) of this AD.
Inspection
(h) Inspect the MLG shock strut cylinders
for cracks using the Option 1 or Option 2
non-destructive testing inspection described
in Boeing Alert Service Bulletin DC9–
32A350, Revision 1, dated August 3, 2005; or
Revision 2, dated March 20, 2009; except as
required by paragraph (m) of this AD. Inspect
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
DC9–32A350, Revision 1, dated August 3,
2005; or Revision 2, dated March 20, 2009;
except as required by paragraph (m) of this
AD. After the effective date of this AD, use
only Boeing Alert Service Bulletin DC9–
32A350, Revision 2, dated March 20, 2009.
Do the detailed inspection before the
accumulation of 60,000 total landings on the
MLG, or at the applicable grace period
specified in Table 1 of this AD, whichever
occurs later, except as required by paragraph
(m) of this AD, and except as provided by
paragraph (k) of this AD. If the review of
maintenance records is not sufficient to
conclusively determine the service history
and number of landings on the MLG shock
strut cylinder, perform the initial inspection
at the applicable grace period specified in
Table 1 of this AD.
TABLE 1—THRESHOLD AND REPETITIVE INTERVAL
Airplanes identified in the Service
Bulletin as Group
Threshold
1 ..............................................................
Within 18 months or 650 landings after October 21, 2005 (the effective date of AD 2005–19–08), whichever occurs first.
Within 18 months or 500 landings after October 21, 2005, whichever occurs first.
Within 18 months or 2,500 landings after October 21, 2005, whichever occurs first.
Within 18 months or 2,100 landings after October 21, 2005, whichever occurs first.
2 ..............................................................
3, except as provided by paragraph (k)
of this AD.
4 ..............................................................
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No Indication of Cracking Is Found
(i) If no indication of cracking is found
during the inspection required by paragraph
(h) of this AD, repeat the inspection in
accordance with Boeing Alert Service
Bulletin DC9–32A350, Revision 1, dated
August 3, 2005; or Boeing Alert Service
Bulletin DC9–32A350, Revision 2, dated
March 20, 2009; at the applicable interval
specified in Table 1 of this AD, except as
required by paragraph (m) of this AD. After
the effective date of this AD, use only Boeing
Alert Service Bulletin DC9–32A350, Revision
2, dated March 20, 2009.
Related Investigative and Corrective Actions
(j) If any indication of cracking is found
during any inspection required by paragraph
(h) or (i) of this AD: Before further flight,
confirm the indication of cracking by doing
all applicable related investigative actions
and doing the applicable corrective actions in
accordance with Boeing Alert Service
Bulletin DC9–32A350, Revision 1, dated
August 3, 2005; or Revision 2, dated
March 20, 2009; except as required by
paragraph (m) of this AD. After the effective
date of this AD, use only Boeing Alert
VerDate Nov<24>2008
17:09 Dec 03, 2009
Jkt 220001
Repetitive interval
Service Bulletin DC9–32A350, Revision 2,
dated March 20, 2009. Repeat the inspection
at the applicable threshold and interval
specified in paragraph (h) of this AD.
MLG Cylinder Previously Installed on Group
4 Airplanes
(k) For MLG cylinders on Group 3
airplanes as identified in Boeing Alert
Service Bulletin DC9–32A350, Revision 1,
dated August 3, 2005; or Revision 2, dated
March 20, 2009: If the MLG cylinder was
previously installed on a Group 4 airplane,
as identified in Boeing Alert Service Bulletin
DC9–32A350, Revision 1, dated August 3,
2005; or Revision 2, dated March 20, 2009;
or if the service history and number of
landings cannot be determined, the MLG
cylinder must be inspected at the grace
period and repetitive interval that applies to
Group 4 airplanes, as specified in Table 1 of
this AD, except as required by paragraph (m)
of this AD.
Actions Accomplished in Accordance With
Original Issue of Service Bulletin
(l) For airplanes with shock struts that have
part numbers other than 5924400–505 and
PO 00000
Frm 00050
Fmt 4700
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Intervals not
landings.
Intervals not
landings.
Intervals not
landings.
Intervals not
landings.
to exceed 650
to exceed 500
to exceed 2,500
to exceed 2,100
5924400–506: Actions done before the
effective date of this AD in accordance with
Boeing Alert Service Bulletin DC9–32A350,
dated December 3, 2004, are acceptable for
compliance with the corresponding actions
required by paragraphs (h), (i), (j), and (k) of
this by this AD.
New Requirements of This AD
(m) For airplanes with shock struts that
have part numbers 5924400–505 and
5924400–506: Do the actions required by
paragraphs (g), (h), (i), (j), and (k), as
applicable, in accordance with Boeing Alert
Service Bulletin DC9–32A350, Revision 2,
dated March 20, 2009. Do the actions at the
time specified in those paragraphs, except
where Table 1 of this AD specifies a
compliance time after October 21, 2005, the
compliance time for these airplanes is within
the specified compliance time after the
effective date of this AD.
Alternative Methods of Compliance
(AMOCs)
(n)(1) The Manager, Los Angeles Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested
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Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Wahib Mina,
ANM–120L, FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712–
4137; telephone (562) 627–5324; fax (562)
627–5210.
(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 principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Los Angeles
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
Material Incorporated by Reference
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(o) You must use Boeing Alert Service
Bulletin DC9–32A350, Revision 2, dated
March 20, 2009, as applicable, to do the
actions required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, 3855 Lakewood Boulevard, MC
D800–0019, Long Beach, California 90846–
0001; telephone 206–544–5000, extension 2;
fax 206–766–5683; e-mail
dse.boecom@boeing.com; Internet https://
www.myboeingfleet.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
reference 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/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
November 19, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–28564 Filed 12–3–09; 8:45 am]
BILLING CODE 4910–13–P
VerDate Nov<24>2008
17:09 Dec 03, 2009
Jkt 220001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0797; Directorate
Identifier 2009–CE–032–AD; Amendment
39–16118; AD 2009–25–01]
RIN 2120–AA64
Airworthiness Directives; Hawker
Beechcraft Corporation Models 58,
58A, 58P, 58PA, 58TC, 58TCA, 95–B55,
95–B55A, A36, A36TC, B36TC, E55,
E55A, F33A, and V35B Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) to
supersede AD 91–18–19, which applies
to certain Hawker Beechcraft
Corporation (Hawker) (Type Certificate
Numbers 3A15, 3A16, and A23CE
formerly held by Raytheon Aircraft
Company; formerly held by Beech
Aircraft Corporation) Models 58, 58A,
58P, 58PA, 58TC, 58TCA, 95–B55, 95–
B55A, A36, A36TC, B36TC, E55, E55A,
F33A, and V35B airplanes. AD 91–18–
19 currently requires you to do a onetime inspection of the pilot and copilot
shoulder harnesses for an incorrect
washer and replace any incorrect
washer with the correct washer. Since
we issued AD 91–18–19, we have found
that the applicability of AD 91–18–19
was incorrectly stated when the Model
A36TC airplane was omitted from the
Applicability section. Consequently,
this AD would retain the actions and the
serial number (SN) applicability of AD
91–18–19 and realign the SN
applicability for Models A36TC and
B36TC airplanes. We are issuing this AD
to detect and correct an incorrect
washer installed in the pilot and copilot
shoulder harnesses. This incorrect part
could result in a malfunctioning
shoulder harness. Such a malfunction
could lead to occupant injury.
DATES: This AD becomes effective on
January 8, 2010.
As of October 21, 1991 (56 FR 42224,
August 27, 1991), the Director of the
Federal Register approved the
incorporation by reference of Beechcraft
Mandatory Service Bulletin No. 2394,
dated December 1990, listed in this AD.
ADDRESSES: For service information
identified in this AD, contact Hawker
Beechcraft Corporation, P.O. Box 85,
Wichita, Kansas 67201–0085; telephone:
(800) 429–5372 or (316) 676–3140;
PO 00000
Frm 00051
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63581
Internet: https://
pubs.hawkerbeechcraft.com.
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–2009–0797; Directorate
Identifier 2009–CE–032–AD.
FOR FURTHER INFORMATION CONTACT:
Steve Potter, Aerospace Engineer, 1801
Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946–
4124; fax: (316) 946–4107.
SUPPLEMENTARY INFORMATION:
Discussion
On August 20, 2009, we issued a
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an AD that would apply to
certain Hawker (Type Certificate
Numbers 3A15, 3A16, and A23CE
formerly held by Raytheon Aircraft
Company; formerly held by Beech
Aircraft Corporation) Models 58, 58A,
58P, 58PA, 58TC, 58TCA, 95–B55, 95–
B55A, A36, A36TC, B36TC, E55, E55A,
F33A, and V35B airplanes. This
proposal was published in the Federal
Register as a notice of proposed
rulemaking (NPRM) on August 28, 2009
(74 FR 44311). The NPRM proposed to
supersede AD 91–18–19 (56 FR 42224,
August 27, 1991) with a new AD that
would retain the actions and the SN
applicability of AD 91–18–19 and
realign the SN applicability for Models
A36TC and B36TC airplanes.
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
We estimate that this AD affects 4,792
airplanes in the U.S. registry.
We estimate the following costs to do
the inspection:
E:\FR\FM\04DER1.SGM
04DER1
]]>Agencies
[Federal Register Volume 74, Number 232 (Friday, December 4, 2009)]
[Rules and Regulations]
[Pages 63578-63581]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-28564]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0658; Directorate Identifier 2009-NM-058-AD;
Amendment 39-16115; AD 2009-24-21]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-9-14, DC-9-
15, and DC-9-15F Airplanes; and McDonnell Douglas Model DC-9-20, DC-9-
30, DC-9-40, and DC-9-50 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) that applies to all McDonnell Douglas Model DC-9-14, DC-9-15, and
DC-9-15F airplanes; and McDonnell Douglas Model DC-9-20, DC-9-30, DC-9-
40, and DC-9-50 series airplanes. That AD currently requires repetitive
inspections for cracks of the main landing gear (MLG) shock strut
cylinder, and related investigative and corrective actions if
necessary. This AD adds more work on airplanes that have main landing
gear shock struts with certain identified part numbers. This AD results
from two reports of a collapsed MLG and a report of cracks in two MLG
cylinders. We are
[[Page 63579]]
issuing this AD to detect and correct fatigue cracks in the shock strut
cylinder of the MLG, which could result in a collapsed MLG during
takeoff or landing, and possible reduced structural integrity of the
airplane.
DATES: This AD becomes effective January 8, 2010.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of January 8,
2010.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; e-mail
dse.boecom@boeing.com; Internet https://www.myboeingfleet.com.
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, 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 2005-19-08, amendment
39-14273 (70 FR 54616, September 16, 2005). The existing AD applies to
all McDonnell Douglas Model DC-9-14, DC-9-15, and DC-9-15F airplanes;
and Model DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes. That
NPRM was published in the Federal Register on July 30, 2009 (74 FR
37963). That NPRM proposed to continue to require repetitive
inspections for cracks of the main landing gear (MLG) shock strut
cylinder, and related investigative and corrective actions if
necessary. That NPRM also proposed to require more work on airplanes
that have main landing gear shock struts with certain identified part
numbers.
Comments
We provided the public the opportunity to participate in the
development of this AD. No comments have been received on the NPRM 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.
Costs of Compliance
There are about 644 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.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Average U.S.-
Action Work hours labor rate Parts Cost per airplane registered Fleet cost
per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection..................... 4 to 6............ $80 None.............. $320 to $480 per 426 $136,320 to $204,480 per
inspection cycle. inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
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 39-14273 (70 FR 54616, September 16, 2005) and by
[[Page 63580]]
adding the following new airworthiness directive (AD):
2009-24-21 McDonnell Douglas: Amendment 39-16115. Docket No. FAA-
2009-0658; Directorate Identifier 2009-NM-058-AD.
Effective Date
(a) This AD becomes effective January 8, 2010.
Affected ADs
(b) This AD supersedes AD 2005-19-08.
Applicability
(c) This AD applies to all McDonnell Douglas Model 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; and
Model DC-9-51 airplanes; certificated in any category.
Subject
(d) Air Transport Association (ATA) of America Code 32: Landing
gear.
Unsafe Condition
(e) This AD results from two reports of a collapsed main landing
gear (MLG) and a report of cracks in two MLG cylinders. We are
issuing this AD to detect and correct fatigue cracks in the shock
strut cylinder of the MLG, which could result in a collapsed MLG
during takeoff or landing, and possible reduced structural integrity
of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2005-19-08, With Revised Service
Information
Records Review
(g) Except as required by paragraph (m) of this AD, before the
applicable compliance time specified in paragraph (h) or Table 1 of
this AD, as applicable, do the applicable actions in paragraphs
(g)(1) and (g)(2) of this AD.
(1) For all airplane groups: Review the airplane maintenance
records of the MLG to determine its service history and the number
of landings on the MLG shock strut cylinder.
(2) For Group 3 airplanes identified in the service bulletin:
Review the maintenance records to determine if the MLG cylinder on
each Group 3 airplane has always been on a Group 3 airplane, and do
the actions in paragraph (k) of this AD.
Inspection
(h) Inspect the MLG shock strut cylinders for cracks using the
Option 1 or Option 2 non-destructive testing inspection described in
Boeing Alert Service Bulletin DC9-32A350, Revision 1, dated August
3, 2005; or Revision 2, dated March 20, 2009; except as required by
paragraph (m) of this AD. Inspect in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin DC9-
32A350, Revision 1, dated August 3, 2005; or Revision 2, dated March
20, 2009; except as required by paragraph (m) of this AD. After the
effective date of this AD, use only Boeing Alert Service Bulletin
DC9-32A350, Revision 2, dated March 20, 2009. Do the detailed
inspection before the accumulation of 60,000 total landings on the
MLG, or at the applicable grace period specified in Table 1 of this
AD, whichever occurs later, except as required by paragraph (m) of
this AD, and except as provided by paragraph (k) of this AD. If the
review of maintenance records is not sufficient to conclusively
determine the service history and number of landings on the MLG
shock strut cylinder, perform the initial inspection at the
applicable grace period specified in Table 1 of this AD.
Table 1--Threshold and Repetitive Interval
----------------------------------------------------------------------------------------------------------------
Airplanes identified in the
Service Bulletin as Group Threshold Repetitive interval
----------------------------------------------------------------------------------------------------------------
1................................. Within 18 months or 650 Intervals not to exceed 650 landings.
landings after October 21,
2005 (the effective date of
AD 2005-19-08), whichever
occurs first.
2................................. Within 18 months or 500 Intervals not to exceed 500 landings.
landings after October 21,
2005, whichever occurs first.
3, except as provided by paragraph Within 18 months or 2,500 Intervals not to exceed 2,500 landings.
(k) of this AD. landings after October 21,
2005, whichever occurs first.
4................................. Within 18 months or 2,100 Intervals not to exceed 2,100 landings.
landings after October 21,
2005, whichever occurs first.
----------------------------------------------------------------------------------------------------------------
No Indication of Cracking Is Found
(i) If no indication of cracking is found during the inspection
required by paragraph (h) of this AD, repeat the inspection in
accordance with Boeing Alert Service Bulletin DC9-32A350, Revision
1, dated August 3, 2005; or Boeing Alert Service Bulletin DC9-
32A350, Revision 2, dated March 20, 2009; at the applicable interval
specified in Table 1 of this AD, except as required by paragraph (m)
of this AD. After the effective date of this AD, use only Boeing
Alert Service Bulletin DC9-32A350, Revision 2, dated March 20, 2009.
Related Investigative and Corrective Actions
(j) If any indication of cracking is found during any inspection
required by paragraph (h) or (i) of this AD: Before further flight,
confirm the indication of cracking by doing all applicable related
investigative actions and doing the applicable corrective actions in
accordance with Boeing Alert Service Bulletin DC9-32A350, Revision
1, dated August 3, 2005; or Revision 2, dated March 20, 2009; except
as required by paragraph (m) of this AD. After the effective date of
this AD, use only Boeing Alert Service Bulletin DC9-32A350, Revision
2, dated March 20, 2009. Repeat the inspection at the applicable
threshold and interval specified in paragraph (h) of this AD.
MLG Cylinder Previously Installed on Group 4 Airplanes
(k) For MLG cylinders on Group 3 airplanes as identified in
Boeing Alert Service Bulletin DC9-32A350, Revision 1, dated August
3, 2005; or Revision 2, dated March 20, 2009: If the MLG cylinder
was previously installed on a Group 4 airplane, as identified in
Boeing Alert Service Bulletin DC9-32A350, Revision 1, dated August
3, 2005; or Revision 2, dated March 20, 2009; or if the service
history and number of landings cannot be determined, the MLG
cylinder must be inspected at the grace period and repetitive
interval that applies to Group 4 airplanes, as specified in Table 1
of this AD, except as required by paragraph (m) of this AD.
Actions Accomplished in Accordance With Original Issue of Service
Bulletin
(l) For airplanes with shock struts that have part numbers other
than 5924400-505 and 5924400-506: Actions done before the effective
date of this AD in accordance with Boeing Alert Service Bulletin
DC9-32A350, dated December 3, 2004, are acceptable for compliance
with the corresponding actions required by paragraphs (h), (i), (j),
and (k) of this by this AD.
New Requirements of This AD
(m) For airplanes with shock struts that have part numbers
5924400-505 and 5924400-506: Do the actions required by paragraphs
(g), (h), (i), (j), and (k), as applicable, in accordance with
Boeing Alert Service Bulletin DC9-32A350, Revision 2, dated March
20, 2009. Do the actions at the time specified in those paragraphs,
except where Table 1 of this AD specifies a compliance time after
October 21, 2005, the compliance time for these airplanes is within
the specified compliance time after the effective date of this AD.
Alternative Methods of Compliance (AMOCs)
(n)(1) The Manager, Los Angeles Aircraft Certification Office,
FAA, has the authority to approve AMOCs for this AD, if requested
[[Page 63581]]
using the procedures found in 14 CFR 39.19. Send information to
ATTN: Wahib Mina, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone (562) 627-5324; fax (562) 627-5210.
(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 principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized
by the Manager, Los Angeles ACO, to make those findings. For a
repair method to be approved, the repair must meet the certification
basis of the airplane, and the approval must specifically refer to
this AD.
Material Incorporated by Reference
(o) You must use Boeing Alert Service Bulletin DC9-32A350,
Revision 2, dated March 20, 2009, as applicable, to do the actions
required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; e-mail
dse.boecom@boeing.com; Internet https://www.myboeingfleet.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(4) You may also review copies of the service information that
is incorporated by reference 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/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on November 19, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-28564 Filed 12-3-09; 8:45 am]
BILLING CODE 4910-13-P
