[Federal Register: September 2, 2005 (Volume 70, Number 170)]
[Rules and Regulations]
[Page 52285-52288]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr02se05-2]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19536; Directorate Identifier 2004-NM-86-AD;
Amendment 39-14247; AD 2005-18-07]
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; DC-8-50 Series Airplanes; DC-8F-54 and DC-8F-55 Airplanes;
DC-8-60 Series Airplanes; DC-8-60F Series Airplanes; DC-8-70 Series
Airplanes; and DC-8-70F Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain McDonnell Douglas transport category
airplanes. That AD currently requires repetitive inspections for
cracking of the lower cargo doorjamb corners, and corrective action if
necessary. That AD provides for optional terminating action for certain
repetitive inspections for certain airplanes. For certain other
airplanes, that AD requires modification of the lower cargo doorjamb
corners. This new AD adds airplanes to the applicability. The existing
AD was prompted by reports of fatigue cracks in the fuselage skin in
the lower cargo doorjamb corners; this AD is prompted by the
inadvertent omission of certain airplanes from the existing
applicability. We are issuing this AD to ensure that the unsafe
condition will be addressed on all affected airplanes so that cracking
in the lower cargo doorjamb corners is detected and corrected before it
can result in rapid decompression of the fuselage and consequent
reduced structural integrity of the airplane.
DATES: Effective October 7, 2005.
On April 29, 2004 (69 FR 15234, March 25, 2004), the Director of
the
[[Page 52286]]
Federal Register approved the incorporation by reference of McDonnell
Douglas Service Bulletin DC8-53-078, Revision 01, dated January 25,
2001.
ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov
or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Boeing Commercial Airplanes, Long Beach Division, 3855
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and
Service Management, Dept. C1-L5A (D800-0024), for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT: Jon Mowery, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone (562) 627-5322; fax (562) 627-5210.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the AD docket on the Internet at http://dms.dot.gov
or in person at the Docket Management Facility office between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays. The Docket
Management Facility office (telephone (800) 647-5227) is located on the
plaza level of the Nassif Building at the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 2004-06-06, amendment
39-13532 (69 FR 15234, March 25, 2004). The existing AD applies to
certain McDonnell Douglas transport category airplanes. That NPRM was
published in the Federal Register on November 5, 2004 (69 FR 64523).
That NPRM proposed to add new airplanes to the applicability of AD
2004-06-06, and retained the requirements for repetitive inspections
for cracking of the lower cargo doorjamb corners, and corrective action
if necessary. That NPRM also retained the provision for optional
terminating action for certain repetitive inspections for certain
airplanes. For certain other airplanes, that NPRM retained the
requirement to modify the lower cargo doorjamb corners.
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 Remove the Reporting Requirements
Two commenters request that the reporting requirements be removed
from the NPRM. One commenter requests that, if the reporting
requirements must be retained, the compliance time to report (within 10
days of the inspection) be extended to 30 days. One commenter states
that the reporting of negative findings would provide very little
useful information while imposing additional workload and cost to the
operators and to the FAA. The other commenter also notes that similar
ADs requiring inspections on principal structural elements on door
corners do not mandate reporting requirements.
We agree with the commenter for the reasons stated, and have
removed the reporting requirements from this AD.
Changes to Delegation Authority
Boeing has received a Delegation Option Authorization (DOA). We
have revised this final rule to delegate the authority to approve an
alternative method of compliance for any repair required by this AD to
the Authorized Representative for the Boeing DOA Organization rather
than the Designated Engineering Representative (DER).
Explanation of Change to the Applicability
We have specified model designations in the applicability of this
AD as published in the most recent type certificate data sheet for the
affected models.
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
This AD affects about 264 airplanes worldwide. The following table
provides the estimated costs for U.S. operators to comply with this AD,
which adds no economic burden above that imposed by AD 2004-06-06. The
current costs for this AD are repeated for the convenience of affected
operators, as follows:
Estimated Costs
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Average Number of affected
Action Work hours labor rate Parts Cost per airplane U.S.-registered Fleet cost
per hour airplanes
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Pre-modification inspections.. 24 $65 None required......... $1,560, per inspection Unknown............... Unknown.
cycle.
Modification.................. 520 65 $25,000............... $58,800............... Unknown............... Unknown.
Post-modification inspections. 40 65 None required......... $2,600, per inspection 244................... $634,400, per
cycle. inspection cycle.
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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
[[Page 52287]]
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 39-13532 (69 FR 15234, March 25, 2004) and by adding
the following new airworthiness directive (AD):
2005-18-07 McDonnell Douglas: Amendment 39-14247. Docket No. FAA-
2004-19536; Directorate Identifier 2004-NM-86-AD.
Effective Date
(a) This AD becomes effective October 7, 2005.
Affected ADs
(b) This AD supersedes AD 2004-06-06, amendment 39-13532.
Applicability
(c) This AD applies to the following McDonnell Douglas
airplanes, certificated in any category; as listed in McDonnell
Douglas Service Bulletin DC8-53-078, Revision 01, dated January 25,
2001:
(1) 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;
(2) Model DC-8-51, DC-8-52, DC-8-53, and DC-8-55 airplanes;
(3) Model DC-8F-54 and DC-8F-55 airplanes;
(4) Model DC-8-61, DC-8-62, and DC-8-63 airplanes;
(5) Model DC-8-61F, DC-8-62F, and DC-8-63F airplanes;
(6) Model DC-8-71, DC-8-72, and DC-8-73 airplanes; and
(7) Model DC-8-71F, DC-8-72F, and DC-8-73F airplanes.
Unsafe Condition
(d) This AD was prompted by reports of fatigue cracks in the
fuselage skin in the lower cargo doorjamb corners. We are issuing
this AD to detect and correct cracking in the lower cargo doorjamb
corners, which could result in rapid decompression of the fuselage
and consequent reduced structural integrity of the airplane.
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.
Restatement of Requirements of AD 2004-06-06
Note 1: This AD is related to AD 93-01-15, amendment 39-8469,
and will affect Principal Structural Elements (PSEs) 53.08.042 and
53.08.043 of the DC-8 Supplemental Inspection Document (SID), Report
L26-011, Volume II, Revision 7, dated April 1993.
Group 1 Airplanes: Inspections and Optional Terminating Action
(f) Except as provided by paragraph (l) of this AD: For
airplanes identified as Group 1 in McDonnell Douglas Service
Bulletin DC8-53-078, Revision 01, dated January 25, 2001:
(1) Within 2,000 landings or 3 years after April 29, 2004 (the
effective date of AD 2004-06-06, amendment 39-13532), whichever
occurs first, perform applicable inspections for cracking of the
lower cargo doorjamb corners, in accordance with the Accomplishment
Instructions of the service bulletin.
(i) If no crack is detected during any inspection required by
this paragraph: Repeat the inspections within the intervals
specified in paragraph 1.E. of the service bulletin.
(ii) If any crack is detected during any inspection required by
this paragraph: Repair before further flight in accordance with the
Accomplishment Instructions of the service bulletin.
(2) Modification of the lower cargo doorjamb corners in
accordance with the Accomplishment Instructions of the service
bulletin terminates the repetitive inspection requirement of
paragraph (f)(1)(i) of this AD.
(3) For airplanes repaired or modified in accordance with
paragraph (f)(1)(ii) or (f)(2) of this AD: Within 17,000 landings
after the repair or modification, perform an eddy current inspection
for cracks of the doorjamb corners, in accordance with the
Accomplishment Instructions of the service bulletin (Drawing
SN08530001). Repeat the inspection at intervals not to exceed 4,400
landings.
Group 2 Airplanes: Modification
(g) Except as provided by paragraph (l) of this AD, for
airplanes identified as Group 2 in McDonnell Douglas Service
Bulletin DC8-53-078, Revision 01, dated January 25, 2001:
(1) Within 2,000 landings or 3 years after April 29, 2004,
whichever occurs first, modify the lower cargo doorjamb corners in
accordance with the Accomplishment Instructions of the service
bulletin.
(2) Within 17,000 landings after the modification required by
paragraph (g)(1) of this AD, perform applicable inspections for
cracking of the doorjamb corners, in accordance with the
Accomplishment Instructions of the service bulletin. Repeat the
inspections at intervals not to exceed 4,400 landings.
Group 3 and Group 4 Airplanes: Inspections
(h) For airplanes identified as Group 3 and Group 4 in McDonnell
Douglas Service Bulletin DC8-53-078, Revision 01, dated January 25,
2001: Within 17,000 landings following accomplishment of the
modification specified in the service bulletin, perform applicable
inspections for cracking of the lower cargo doorjamb corners, in
accordance with the Accomplishment Instructions of the service
bulletin. Repeat the inspections at intervals not to exceed 4,400
landings.
All Airplanes: Repair Following Post-Modification Inspections
(i) If any cracking is detected during any inspection required
by paragraph (f)(3), (g)(2), or (h) of this AD: Repair before
further flight in accordance with a method approved by the Manager,
Los Angeles Aircraft Certification Office (ACO), FAA; or per data
meeting the type certification basis of the airplane approved by an
Authorized Representative for the Boeing 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.
Credit for Prior Accomplishment
(j) Inspections done before the effective date of April 29,
2004, in accordance with McDonnell Douglas Service Bulletin DC8-53-
078, dated February 6, 1996, are acceptable for compliance with the
applicable inspections required by this AD.
(k) Inspections and repairs specified in this AD of areas of
PSEs 53.08.042 and 53.08.043 are acceptable for compliance with the
applicable requirements of paragraphs (a) and (b) of AD 93-01-15.
The remaining areas of the affected PSEs must be inspected and
repaired as applicable, in accordance with AD 93-01-15.
Requirements for Newly Added Airplanes
(l) For airplanes not subject to the requirements of AD 2004-06-
06, the reference time for compliance is the effective date of this
new AD, rather than April 29, 2004 (the effective date of AD 2004-
06-06).
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, Los Angeles Aircraft Certification (ACO),
Transport Airplane
[[Page 52288]]
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) 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 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
(n) You must use McDonnell Douglas Service Bulletin DC8-53-078,
Revision 01, dated January 25, 2001, to perform the actions that are
required by this AD, unless the AD specifies otherwise. The Director
of the Federal Register previously approved the incorporation by
reference of this document as of April 29, 2004 (69 FR 15234, March
25, 2004). Contact Boeing Commercial Airplanes, Long Beach Division,
3855 Lakewood Boulevard, Long Beach, California 90846, Attention:
Data and Service Management, Dept. C1-L5A (D800-0024), for a copy of
this service information. You may review copies at the Docket
Management Facility, U.S. Department of Transportation, 400 Seventh
Street, SW., room PL-401, Nassif Building, Washington, DC; on the
Internet at http://dms.dot.gov; or at the National Archives and
Records Administration (NARA). For information on the availability
of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Issued in Renton, Washington, on August 24, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-17401 Filed 9-1-05; 8:45 am]
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